FX 60-160 AIRFOIL (fx60160-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: FX 60-160 AIRFOIL (fx60160-il) Reynolds number: 1,000,000 Max Cl/Cd: 116.67 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx60160-il-1000000.txt Download as CSV file: xf-fx60160-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: FX 60-160 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.000 -0.8351 0.08983 0.08743 -0.0749 1.0000 0.0135
-17.750 -0.8714 0.07975 0.07719 -0.0806 1.0000 0.0134
-17.500 -0.9025 0.07127 0.06854 -0.0853 1.0000 0.0135
-17.250 -0.9279 0.06427 0.06139 -0.0889 1.0000 0.0136
-17.000 -0.9456 0.05885 0.05585 -0.0914 1.0000 0.0136
-16.750 -0.9623 0.05396 0.05086 -0.0933 1.0000 0.0139
-16.500 -0.9735 0.05015 0.04696 -0.0944 1.0000 0.0140
-16.250 -0.9779 0.04745 0.04420 -0.0947 1.0000 0.0142
-16.000 -0.9823 0.04504 0.04174 -0.0945 1.0000 0.0144
-15.750 -0.9882 0.04271 0.03934 -0.0939 1.0000 0.0145
-15.500 -0.9928 0.04072 0.03729 -0.0930 1.0000 0.0147
-15.250 -0.9921 0.03933 0.03587 -0.0918 1.0000 0.0149
-15.000 -0.9994 0.03738 0.03384 -0.0902 1.0000 0.0150
-14.750 -0.9993 0.03615 0.03257 -0.0887 1.0000 0.0153
-14.500 -0.9848 0.03417 0.03049 -0.0908 0.9989 0.0156
-14.250 -0.9631 0.03287 0.02911 -0.0930 0.9976 0.0161
-14.000 -0.9412 0.03152 0.02767 -0.0953 0.9960 0.0164
-13.750 -0.9187 0.03014 0.02618 -0.0976 0.9944 0.0166
-13.500 -0.9089 0.02767 0.02361 -0.0995 0.9918 0.0173
-13.250 -0.8875 0.02654 0.02244 -0.1012 0.9892 0.0177
-13.000 -0.8620 0.02559 0.02147 -0.1033 0.9870 0.0181
-12.750 -0.8343 0.02472 0.02056 -0.1057 0.9852 0.0186
-12.500 -0.8062 0.02366 0.01941 -0.1083 0.9836 0.0191
-12.250 -0.7755 0.02281 0.01849 -0.1110 0.9824 0.0197
-12.000 -0.7576 0.02191 0.01750 -0.1113 0.9774 0.0200
-11.750 -0.7290 0.02124 0.01676 -0.1134 0.9746 0.0203
-11.500 -0.7038 0.01954 0.01497 -0.1156 0.9723 0.0213
-11.250 -0.6699 0.01900 0.01442 -0.1182 0.9706 0.0219
-11.000 -0.6416 0.01843 0.01382 -0.1195 0.9672 0.0224
-10.750 -0.6173 0.01788 0.01321 -0.1199 0.9616 0.0230
-10.500 -0.5873 0.01735 0.01262 -0.1213 0.9576 0.0237
-10.250 -0.5606 0.01690 0.01211 -0.1219 0.9520 0.0242
-10.000 -0.5374 0.01664 0.01178 -0.1216 0.9442 0.0246
-9.750 -0.5190 0.01546 0.01050 -0.1209 0.9361 0.0255
-9.500 -0.4974 0.01495 0.00996 -0.1204 0.9263 0.0261
-9.250 -0.4759 0.01461 0.00959 -0.1197 0.9145 0.0267
-9.000 -0.4526 0.01430 0.00922 -0.1192 0.9013 0.0274
-8.750 -0.4298 0.01394 0.00878 -0.1187 0.8852 0.0281
-8.500 -0.4075 0.01360 0.00833 -0.1180 0.8678 0.0287
-8.250 -0.3850 0.01334 0.00796 -0.1173 0.8510 0.0293
-8.000 -0.3613 0.01322 0.00773 -0.1168 0.8365 0.0298
-7.750 -0.3433 0.01252 0.00692 -0.1155 0.8238 0.0306
-7.500 -0.3224 0.01209 0.00643 -0.1147 0.8135 0.0316
-7.250 -0.2990 0.01183 0.00612 -0.1142 0.8041 0.0323
-7.000 -0.2747 0.01161 0.00585 -0.1138 0.7962 0.0332
-6.750 -0.2500 0.01141 0.00559 -0.1134 0.7885 0.0341
-6.500 -0.2250 0.01120 0.00534 -0.1131 0.7821 0.0351
-6.250 -0.1996 0.01101 0.00510 -0.1129 0.7757 0.0358
-6.000 -0.1758 0.01069 0.00469 -0.1125 0.7695 0.0366
-5.750 -0.1517 0.01027 0.00426 -0.1121 0.7641 0.0384
-5.500 -0.1258 0.01008 0.00405 -0.1120 0.7586 0.0398
-5.250 -0.0996 0.00995 0.00386 -0.1118 0.7533 0.0414
-5.000 -0.0728 0.00980 0.00370 -0.1118 0.7487 0.0428
-4.750 -0.0462 0.00965 0.00351 -0.1118 0.7438 0.0439
-4.500 -0.0209 0.00935 0.00316 -0.1115 0.7389 0.0471
-4.250 0.0059 0.00920 0.00299 -0.1115 0.7344 0.0495
-4.000 0.0331 0.00907 0.00285 -0.1116 0.7299 0.0520
-3.750 0.0598 0.00890 0.00265 -0.1115 0.7252 0.0560
-3.500 0.0865 0.00877 0.00250 -0.1114 0.7205 0.0610
-3.250 0.1138 0.00862 0.00235 -0.1115 0.7162 0.0670
-3.000 0.1402 0.00838 0.00220 -0.1114 0.7115 0.0901
-2.750 0.1605 0.00733 0.00183 -0.1109 0.7070 0.2995
-2.500 0.1840 0.00669 0.00164 -0.1107 0.7028 0.4306
-2.250 0.2102 0.00641 0.00157 -0.1106 0.6986 0.5015
-2.000 0.2373 0.00632 0.00156 -0.1105 0.6942 0.5369
-1.750 0.2648 0.00631 0.00156 -0.1105 0.6898 0.5636
-1.500 0.2929 0.00631 0.00158 -0.1106 0.6858 0.5797
-1.250 0.3210 0.00632 0.00160 -0.1107 0.6816 0.5933
-1.000 0.3489 0.00635 0.00163 -0.1107 0.6772 0.6050
-0.750 0.3768 0.00642 0.00166 -0.1108 0.6727 0.6135
-0.500 0.4051 0.00644 0.00170 -0.1109 0.6686 0.6216
-0.250 0.4332 0.00647 0.00171 -0.1110 0.6641 0.6268
0.000 0.4608 0.00653 0.00177 -0.1110 0.6596 0.6332
0.250 0.4889 0.00663 0.00183 -0.1111 0.6553 0.6409
0.500 0.5168 0.00664 0.00187 -0.1111 0.6507 0.6459
0.750 0.5445 0.00669 0.00191 -0.1111 0.6459 0.6491
1.000 0.5719 0.00677 0.00196 -0.1111 0.6411 0.6529
1.250 0.6001 0.00681 0.00200 -0.1112 0.6368 0.6564
1.500 0.6276 0.00683 0.00203 -0.1112 0.6316 0.6597
1.750 0.6545 0.00690 0.00208 -0.1111 0.6263 0.6627
2.000 0.6822 0.00694 0.00214 -0.1112 0.6212 0.6657
2.250 0.7090 0.00700 0.00219 -0.1110 0.6139 0.6689
2.500 0.7356 0.00708 0.00225 -0.1108 0.6061 0.6719
2.750 0.7617 0.00714 0.00229 -0.1105 0.5970 0.6748
3.000 0.7874 0.00720 0.00235 -0.1101 0.5862 0.6780
3.250 0.8123 0.00730 0.00243 -0.1096 0.5732 0.6806
3.500 0.8370 0.00741 0.00251 -0.1090 0.5606 0.6833
3.750 0.8620 0.00753 0.00260 -0.1086 0.5491 0.6859
4.000 0.8870 0.00765 0.00270 -0.1081 0.5364 0.6882
4.250 0.9106 0.00781 0.00280 -0.1073 0.5205 0.6903
4.500 0.9322 0.00799 0.00293 -0.1062 0.5008 0.6927
4.750 0.9529 0.00824 0.00309 -0.1049 0.4749 0.6949
5.000 0.9718 0.00856 0.00330 -0.1033 0.4464 0.6973
5.250 0.9905 0.00888 0.00351 -0.1017 0.4211 0.6997
5.500 1.0082 0.00924 0.00375 -0.0998 0.3939 0.7020
5.750 1.0217 0.00966 0.00402 -0.0972 0.3613 0.7041
6.000 1.0326 0.01014 0.00432 -0.0941 0.3227 0.7062
6.250 1.0352 0.01095 0.00483 -0.0895 0.2626 0.7089
6.500 1.0298 0.01211 0.00560 -0.0837 0.1869 0.7112
6.750 1.0198 0.01353 0.00657 -0.0773 0.1004 0.7136
7.000 1.0278 0.01426 0.00718 -0.0741 0.0753 0.7160
7.250 1.0424 0.01474 0.00764 -0.0721 0.0653 0.7185
7.500 1.0571 0.01523 0.00811 -0.0701 0.0580 0.7206
7.750 1.0726 0.01567 0.00855 -0.0683 0.0536 0.7230
8.000 1.0859 0.01622 0.00910 -0.0662 0.0489 0.7256
8.250 1.1026 0.01663 0.00956 -0.0646 0.0475 0.7281
8.500 1.1183 0.01710 0.01006 -0.0630 0.0457 0.7306
8.750 1.1326 0.01766 0.01061 -0.0612 0.0433 0.7333
9.000 1.1441 0.01838 0.01135 -0.0591 0.0410 0.7357
9.250 1.1578 0.01899 0.01202 -0.0573 0.0401 0.7384
9.500 1.1726 0.01955 0.01263 -0.0558 0.0396 0.7411
9.750 1.1876 0.02013 0.01326 -0.0544 0.0388 0.7440
10.000 1.2011 0.02081 0.01399 -0.0528 0.0379 0.7470
10.250 1.2152 0.02149 0.01469 -0.0514 0.0367 0.7501
10.500 1.2277 0.02228 0.01551 -0.0498 0.0359 0.7529
10.750 1.2386 0.02317 0.01645 -0.0482 0.0351 0.7564
11.000 1.2471 0.02425 0.01759 -0.0463 0.0341 0.7599
11.250 1.2535 0.02552 0.01894 -0.0444 0.0332 0.7638
11.500 1.2680 0.02630 0.01977 -0.0433 0.0328 0.7678
11.750 1.2826 0.02706 0.02059 -0.0424 0.0321 0.7722
12.000 1.2941 0.02806 0.02166 -0.0411 0.0317 0.7770
12.250 1.3077 0.02894 0.02258 -0.0402 0.0307 0.7824
12.500 1.3194 0.02996 0.02367 -0.0391 0.0300 0.7888
12.750 1.3304 0.03105 0.02480 -0.0380 0.0290 0.7970
13.000 1.3384 0.03238 0.02621 -0.0368 0.0281 0.8080
13.250 1.3410 0.03413 0.02808 -0.0351 0.0272 0.8257
13.500 1.3745 0.03468 0.02897 -0.0380 0.0264 0.9282
13.750 1.4010 0.03571 0.03004 -0.0399 0.0249 1.0000
14.000 1.4131 0.03696 0.03129 -0.0393 0.0236 1.0000
14.250 1.4231 0.03839 0.03273 -0.0387 0.0219 1.0000
14.500 1.4364 0.03955 0.03391 -0.0382 0.0194 1.0000
14.750 1.4442 0.04121 0.03556 -0.0375 0.0157 1.0000
15.000 1.4487 0.04323 0.03756 -0.0367 0.0130 1.0000
15.250 1.4505 0.04554 0.03989 -0.0359 0.0112 1.0000
15.500 1.4539 0.04776 0.04217 -0.0352 0.0106 1.0000
15.750 1.4543 0.05032 0.04476 -0.0346 0.0097 1.0000
16.000 1.4546 0.05298 0.04748 -0.0340 0.0092 1.0000
16.250 1.4588 0.05528 0.04986 -0.0337 0.0090 1.0000
16.500 1.4609 0.05785 0.05251 -0.0334 0.0088 1.0000
16.750 1.4628 0.06048 0.05522 -0.0332 0.0085 1.0000
17.000 1.4636 0.06329 0.05810 -0.0331 0.0083 1.0000
17.250 1.4637 0.06624 0.06113 -0.0331 0.0081 1.0000
17.500 1.4636 0.06929 0.06426 -0.0332 0.0080 1.0000
17.750 1.4613 0.07265 0.06769 -0.0334 0.0077 1.0000
18.000 1.4577 0.07627 0.07140 -0.0338 0.0076 1.0000
18.250 1.4504 0.08048 0.07570 -0.0344 0.0073 1.0000
18.500 1.4463 0.08435 0.07967 -0.0351 0.0072 1.0000
|
Polar data table (+)
Polar graphs
<< Back to FX 60-160 AIRFOIL (fx60160-il)