GOE 619 AIRFOIL (goe619-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 619 AIRFOIL (goe619-il) Reynolds number: 1,000,000 Max Cl/Cd: 99.6 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe619-il-1000000-n5.txt Download as CSV file: xf-goe619-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 619 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.750 -0.6664 0.12698 0.12477 -0.0452 1.0000 0.0198
-17.500 -0.6934 0.11808 0.11578 -0.0499 1.0000 0.0203
-17.250 -0.7160 0.11030 0.10792 -0.0540 1.0000 0.0205
-17.000 -0.7354 0.10334 0.10088 -0.0576 1.0000 0.0208
-16.750 -0.7565 0.09630 0.09376 -0.0614 1.0000 0.0209
-16.500 -0.7768 0.08959 0.08697 -0.0650 1.0000 0.0211
-16.250 -0.7958 0.08329 0.08059 -0.0683 1.0000 0.0212
-16.000 -0.8152 0.07718 0.07441 -0.0716 1.0000 0.0213
-15.750 -0.8375 0.07097 0.06812 -0.0750 1.0000 0.0214
-15.500 -0.8650 0.06455 0.06162 -0.0784 1.0000 0.0214
-15.250 -0.8981 0.05779 0.05477 -0.0820 1.0000 0.0214
-15.000 -0.9428 0.05012 0.04701 -0.0857 1.0000 0.0214
-14.750 -1.0061 0.03912 0.03585 -0.0935 0.9991 0.0212
-14.500 -1.0066 0.02917 0.02557 -0.1098 0.9934 0.0214
-14.250 -0.9912 0.02708 0.02336 -0.1116 0.9886 0.0216
-14.000 -0.9677 0.02566 0.02183 -0.1135 0.9852 0.0218
-13.750 -0.9423 0.02438 0.02045 -0.1153 0.9828 0.0219
-13.500 -0.9238 0.02343 0.01942 -0.1150 0.9769 0.0221
-13.250 -0.9002 0.02231 0.01821 -0.1160 0.9729 0.0223
-13.000 -0.8802 0.02102 0.01683 -0.1163 0.9672 0.0227
-12.750 -0.8555 0.02007 0.01581 -0.1170 0.9617 0.0230
-12.250 -0.7943 0.01855 0.01418 -0.1199 0.9524 0.0236
-12.000 -0.7603 0.01783 0.01339 -0.1219 0.9468 0.0239
-11.750 -0.7258 0.01720 0.01269 -0.1239 0.9407 0.0243
-11.500 -0.6927 0.01659 0.01200 -0.1256 0.9316 0.0246
-11.250 -0.6617 0.01601 0.01133 -0.1268 0.9206 0.0249
-11.000 -0.6336 0.01549 0.01071 -0.1272 0.9084 0.0251
-10.750 -0.6083 0.01504 0.01015 -0.1270 0.8960 0.0254
-10.500 -0.5843 0.01465 0.00967 -0.1265 0.8846 0.0256
-10.250 -0.5603 0.01429 0.00922 -0.1259 0.8739 0.0259
-10.000 -0.5365 0.01397 0.00880 -0.1252 0.8627 0.0261
-9.750 -0.5128 0.01363 0.00837 -0.1245 0.8524 0.0262
-9.500 -0.4889 0.01332 0.00797 -0.1237 0.8427 0.0264
-9.250 -0.4645 0.01303 0.00760 -0.1231 0.8334 0.0265
-9.000 -0.4413 0.01261 0.00710 -0.1223 0.8246 0.0268
-8.750 -0.4177 0.01222 0.00663 -0.1215 0.8151 0.0272
-8.500 -0.3935 0.01188 0.00622 -0.1208 0.8063 0.0276
-8.250 -0.3688 0.01160 0.00587 -0.1201 0.7972 0.0279
-8.000 -0.3437 0.01133 0.00554 -0.1196 0.7893 0.0283
-7.750 -0.3183 0.01109 0.00524 -0.1190 0.7810 0.0286
-7.500 -0.2928 0.01087 0.00496 -0.1184 0.7731 0.0291
-7.250 -0.2670 0.01066 0.00470 -0.1179 0.7643 0.0295
-7.000 -0.2411 0.01047 0.00445 -0.1174 0.7566 0.0300
-6.750 -0.2150 0.01028 0.00421 -0.1169 0.7486 0.0304
-6.500 -0.1889 0.01012 0.00399 -0.1164 0.7412 0.0307
-6.250 -0.1624 0.00996 0.00378 -0.1160 0.7330 0.0311
-6.000 -0.1362 0.00982 0.00358 -0.1155 0.7256 0.0314
-5.750 -0.1095 0.00964 0.00337 -0.1151 0.7182 0.0321
-5.250 -0.0566 0.00933 0.00299 -0.1143 0.7034 0.0343
-5.000 -0.0301 0.00921 0.00283 -0.1138 0.6956 0.0356
-4.750 -0.0033 0.00909 0.00267 -0.1134 0.6885 0.0371
-4.500 0.0231 0.00893 0.00251 -0.1130 0.6805 0.0422
-4.250 0.0486 0.00868 0.00234 -0.1125 0.6732 0.0635
-4.000 0.0753 0.00857 0.00225 -0.1121 0.6646 0.0733
-3.750 0.1019 0.00853 0.00217 -0.1116 0.6539 0.0782
-3.500 0.1277 0.00848 0.00209 -0.1110 0.6401 0.0832
-3.000 0.1805 0.00846 0.00196 -0.1100 0.6138 0.0891
-2.750 0.2071 0.00842 0.00189 -0.1096 0.6034 0.0933
-2.500 0.2338 0.00838 0.00184 -0.1092 0.5950 0.0972
-2.250 0.2610 0.00835 0.00179 -0.1089 0.5887 0.1006
-2.000 0.2883 0.00833 0.00174 -0.1086 0.5815 0.1030
-1.750 0.3150 0.00829 0.00170 -0.1081 0.5744 0.1084
-1.500 0.3420 0.00824 0.00166 -0.1078 0.5663 0.1153
-1.250 0.3682 0.00821 0.00162 -0.1073 0.5562 0.1264
-1.000 0.3942 0.00815 0.00160 -0.1068 0.5447 0.1461
-0.750 0.4201 0.00808 0.00159 -0.1063 0.5337 0.1743
-0.500 0.4461 0.00808 0.00160 -0.1058 0.5220 0.1919
-0.250 0.4718 0.00811 0.00162 -0.1052 0.5082 0.2076
0.000 0.4973 0.00816 0.00165 -0.1046 0.4924 0.2209
0.250 0.5226 0.00825 0.00169 -0.1040 0.4746 0.2306
0.500 0.5475 0.00835 0.00174 -0.1032 0.4556 0.2416
0.750 0.5720 0.00848 0.00181 -0.1025 0.4352 0.2520
1.000 0.5960 0.00864 0.00190 -0.1016 0.4133 0.2617
1.250 0.6199 0.00881 0.00200 -0.1007 0.3916 0.2706
1.500 0.6438 0.00900 0.00210 -0.0999 0.3697 0.2786
1.750 0.6664 0.00922 0.00223 -0.0988 0.3447 0.2895
2.000 0.6899 0.00940 0.00235 -0.0979 0.3247 0.3013
2.250 0.7137 0.00956 0.00247 -0.0970 0.3088 0.3150
2.500 0.7377 0.00969 0.00258 -0.0961 0.2968 0.3280
2.750 0.7621 0.00980 0.00269 -0.0954 0.2863 0.3437
3.250 0.8085 0.01007 0.00297 -0.0935 0.2628 0.3923
3.500 0.8322 0.01019 0.00311 -0.0926 0.2534 0.4125
3.750 0.8552 0.01034 0.00326 -0.0916 0.2437 0.4338
4.000 0.8785 0.01045 0.00340 -0.0907 0.2364 0.4593
4.250 0.9011 0.01058 0.00355 -0.0896 0.2291 0.4845
4.500 0.9242 0.01065 0.00369 -0.0887 0.2245 0.5166
4.750 0.9409 0.01036 0.00390 -0.0865 0.2199 0.7207
5.250 1.0249 0.01036 0.00442 -0.0928 0.2097 1.0000
5.500 1.0466 0.01055 0.00458 -0.0915 0.2050 1.0000
5.750 1.0675 0.01077 0.00476 -0.0901 0.1998 1.0000
6.000 1.0888 0.01094 0.00492 -0.0888 0.1965 1.0000
6.250 1.1086 0.01113 0.00510 -0.0872 0.1919 1.0000
6.500 1.1261 0.01139 0.00531 -0.0852 0.1845 1.0000
6.750 1.1447 0.01163 0.00551 -0.0834 0.1762 1.0000
7.000 1.1615 0.01196 0.00577 -0.0813 0.1657 1.0000
7.250 1.1768 0.01236 0.00608 -0.0791 0.1505 1.0000
7.500 1.1863 0.01302 0.00656 -0.0759 0.1242 1.0000
7.750 1.1795 0.01447 0.00767 -0.0703 0.0672 1.0000
8.000 1.1934 0.01502 0.00817 -0.0681 0.0579 1.0000
8.250 1.2097 0.01547 0.00861 -0.0663 0.0542 1.0000
8.500 1.2269 0.01589 0.00902 -0.0647 0.0514 1.0000
8.750 1.2450 0.01627 0.00941 -0.0632 0.0504 1.0000
9.000 1.2622 0.01670 0.00985 -0.0617 0.0489 1.0000
9.250 1.2790 0.01718 0.01034 -0.0602 0.0473 1.0000
9.500 1.2947 0.01772 0.01087 -0.0586 0.0453 1.0000
9.750 1.3106 0.01827 0.01143 -0.0571 0.0432 1.0000
10.000 1.3275 0.01878 0.01196 -0.0558 0.0422 1.0000
10.250 1.3432 0.01938 0.01255 -0.0544 0.0397 1.0000
10.500 1.3570 0.02010 0.01326 -0.0528 0.0363 1.0000
11.000 1.3708 0.02256 0.01563 -0.0485 0.0130 1.0000
11.250 1.3839 0.02344 0.01654 -0.0471 0.0120 1.0000
11.500 1.3968 0.02436 0.01750 -0.0458 0.0112 1.0000
11.750 1.4092 0.02533 0.01851 -0.0446 0.0108 1.0000
12.000 1.4199 0.02646 0.01969 -0.0433 0.0101 1.0000
12.250 1.4318 0.02754 0.02081 -0.0422 0.0098 1.0000
12.500 1.4431 0.02867 0.02199 -0.0411 0.0095 1.0000
12.750 1.4536 0.02990 0.02327 -0.0400 0.0091 1.0000
13.000 1.4635 0.03121 0.02463 -0.0390 0.0088 1.0000
13.250 1.4722 0.03266 0.02613 -0.0380 0.0085 1.0000
13.500 1.4797 0.03424 0.02776 -0.0370 0.0082 1.0000
13.750 1.4850 0.03606 0.02964 -0.0360 0.0079 1.0000
14.000 1.4921 0.03776 0.03140 -0.0352 0.0078 1.0000
14.250 1.4988 0.03955 0.03325 -0.0346 0.0076 1.0000
14.500 1.5041 0.04151 0.03527 -0.0339 0.0075 1.0000
14.750 1.5090 0.04355 0.03737 -0.0333 0.0073 1.0000
15.000 1.5126 0.04577 0.03966 -0.0328 0.0071 1.0000
15.250 1.5153 0.04815 0.04210 -0.0324 0.0070 1.0000
15.500 1.5172 0.05065 0.04468 -0.0320 0.0069 1.0000
15.750 1.5181 0.05331 0.04740 -0.0318 0.0067 1.0000
16.000 1.5172 0.05623 0.05040 -0.0317 0.0066 1.0000
16.250 1.5153 0.05935 0.05359 -0.0316 0.0065 1.0000
16.500 1.5120 0.06270 0.05703 -0.0317 0.0063 1.0000
16.750 1.5065 0.06636 0.06077 -0.0320 0.0062 1.0000
17.000 1.4982 0.07050 0.06501 -0.0324 0.0061 1.0000
17.250 1.4926 0.07435 0.06895 -0.0329 0.0060 1.0000
17.500 1.4849 0.07855 0.07325 -0.0336 0.0060 1.0000
17.750 1.4750 0.08310 0.07790 -0.0344 0.0060 1.0000
18.000 1.4664 0.08757 0.08247 -0.0354 0.0059 1.0000
18.250 1.4551 0.09253 0.08753 -0.0366 0.0059 1.0000
18.500 1.4448 0.09737 0.09247 -0.0378 0.0058 1.0000
18.750 1.4311 0.10279 0.09800 -0.0394 0.0058 1.0000
19.000 1.4195 0.10800 0.10332 -0.0410 0.0057 1.0000
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