BOEING-VERTOL VR-12 AIRFOIL (vr12-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: BOEING-VERTOL VR-12 AIRFOIL (vr12-il) Reynolds number: 500,000 Max Cl/Cd: 75.49 at α=9° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-vr12-il-500000-n5.txt Download as CSV file: xf-vr12-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: BOEING-VERTOL VR-12 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.250 -0.4216 0.16997 0.16781 0.0139 1.0000 0.0099
-16.000 -0.4179 0.16745 0.16529 0.0127 1.0000 0.0099
-15.500 -0.6191 0.18837 0.18598 0.0383 1.0000 0.0076
-15.250 -0.6104 0.18577 0.18339 0.0373 1.0000 0.0075
-15.000 -0.6025 0.18289 0.18051 0.0358 1.0000 0.0072
-10.500 -0.8975 0.02958 0.02558 -0.0294 0.9870 0.0073
-10.250 -0.8875 0.02585 0.02132 -0.0281 0.9752 0.0076
-10.000 -0.8687 0.02446 0.01976 -0.0271 0.9669 0.0079
-9.750 -0.8487 0.02367 0.01887 -0.0259 0.9593 0.0082
-9.500 -0.8285 0.02280 0.01787 -0.0248 0.9524 0.0086
-9.250 -0.8095 0.02181 0.01671 -0.0233 0.9457 0.0090
-9.000 -0.7896 0.02061 0.01529 -0.0220 0.9390 0.0096
-8.750 -0.7699 0.01951 0.01396 -0.0206 0.9323 0.0102
-8.500 -0.7460 0.01918 0.01360 -0.0199 0.9263 0.0107
-8.250 -0.7220 0.01882 0.01319 -0.0192 0.9201 0.0111
-8.000 -0.6990 0.01835 0.01262 -0.0182 0.9147 0.0117
-7.750 -0.6751 0.01759 0.01170 -0.0174 0.9086 0.0125
-7.500 -0.6517 0.01693 0.01090 -0.0165 0.9026 0.0131
-7.250 -0.6265 0.01674 0.01067 -0.0159 0.8969 0.0136
-7.000 -0.6007 0.01652 0.01042 -0.0155 0.8907 0.0142
-6.750 -0.5757 0.01619 0.01000 -0.0148 0.8854 0.0150
-6.500 -0.5504 0.01561 0.00928 -0.0143 0.8798 0.0159
-6.250 -0.5249 0.01517 0.00875 -0.0137 0.8738 0.0165
-5.750 -0.4718 0.01491 0.00844 -0.0131 0.8624 0.0182
-5.500 -0.4456 0.01458 0.00801 -0.0127 0.8567 0.0193
-5.250 -0.4190 0.01432 0.00763 -0.0122 0.8513 0.0202
-5.000 -0.3933 0.01376 0.00706 -0.0118 0.8447 0.0212
-4.750 -0.3671 0.01344 0.00671 -0.0114 0.8388 0.0219
-4.500 -0.3405 0.01308 0.00630 -0.0111 0.8331 0.0228
-4.250 -0.3137 0.01275 0.00591 -0.0107 0.8272 0.0238
-4.000 -0.2872 0.01245 0.00553 -0.0103 0.8222 0.0247
-3.750 -0.2609 0.01200 0.00504 -0.0099 0.8157 0.0255
-3.500 -0.2352 0.01162 0.00462 -0.0093 0.8071 0.0264
-3.250 -0.2087 0.01135 0.00432 -0.0089 0.7963 0.0273
-3.000 -0.1820 0.01112 0.00404 -0.0085 0.7865 0.0284
-2.750 -0.1551 0.01091 0.00377 -0.0081 0.7770 0.0296
-2.500 -0.1280 0.01070 0.00351 -0.0078 0.7670 0.0305
-2.250 -0.1013 0.01046 0.00321 -0.0075 0.7564 0.0314
-2.000 -0.0744 0.01023 0.00296 -0.0071 0.7456 0.0331
-1.750 -0.0469 0.01007 0.00276 -0.0069 0.7346 0.0347
-1.500 -0.0195 0.00992 0.00258 -0.0067 0.7226 0.0362
-1.250 0.0081 0.00980 0.00240 -0.0065 0.7104 0.0379
-1.000 0.0356 0.00966 0.00223 -0.0063 0.6970 0.0415
-0.750 0.0632 0.00955 0.00209 -0.0061 0.6815 0.0473
-0.500 0.0903 0.00939 0.00196 -0.0059 0.6648 0.0690
-0.250 0.1156 0.00901 0.00185 -0.0054 0.6423 0.1716
0.000 0.1375 0.00834 0.00172 -0.0046 0.6092 0.3739
0.250 0.1490 0.00718 0.00162 -0.0014 0.5690 0.7128
0.500 0.2073 0.00728 0.00206 -0.0075 0.4807 0.9451
0.750 0.2507 0.00795 0.00238 -0.0108 0.4057 0.9664
1.000 0.2945 0.00856 0.00265 -0.0144 0.3408 0.9790
1.250 0.3348 0.00896 0.00282 -0.0172 0.3011 0.9859
1.500 0.3697 0.00918 0.00288 -0.0189 0.2773 0.9880
1.750 0.4022 0.00936 0.00293 -0.0200 0.2604 0.9900
2.000 0.4339 0.00952 0.00300 -0.0210 0.2478 0.9920
2.250 0.4651 0.00967 0.00307 -0.0218 0.2373 0.9939
2.500 0.4981 0.00980 0.00313 -0.0231 0.2280 0.9952
2.750 0.5310 0.00994 0.00320 -0.0243 0.2189 0.9965
3.000 0.5637 0.01006 0.00327 -0.0255 0.2113 0.9979
3.250 0.5957 0.01022 0.00337 -0.0266 0.2033 0.9992
3.500 0.6257 0.01035 0.00346 -0.0272 0.1962 1.0000
3.750 0.6510 0.01050 0.00356 -0.0268 0.1892 1.0000
4.000 0.6761 0.01064 0.00367 -0.0263 0.1836 1.0000
4.250 0.7010 0.01079 0.00379 -0.0259 0.1782 1.0000
4.500 0.7256 0.01097 0.00394 -0.0253 0.1728 1.0000
4.750 0.7504 0.01112 0.00408 -0.0248 0.1687 1.0000
5.000 0.7749 0.01129 0.00424 -0.0243 0.1635 1.0000
5.250 0.7990 0.01151 0.00441 -0.0237 0.1580 1.0000
5.500 0.8233 0.01168 0.00458 -0.0231 0.1538 1.0000
5.750 0.8474 0.01187 0.00477 -0.0225 0.1493 1.0000
6.000 0.8712 0.01210 0.00498 -0.0218 0.1454 1.0000
6.250 0.8949 0.01232 0.00520 -0.0212 0.1423 1.0000
6.500 0.9187 0.01251 0.00542 -0.0205 0.1394 1.0000
6.750 0.9422 0.01274 0.00565 -0.0198 0.1356 1.0000
7.000 0.9653 0.01301 0.00590 -0.0191 0.1315 1.0000
7.250 0.9884 0.01326 0.00616 -0.0183 0.1286 1.0000
7.500 1.0116 0.01348 0.00642 -0.0176 0.1262 1.0000
7.750 1.0344 0.01374 0.00670 -0.0168 0.1237 1.0000
8.000 1.0570 0.01401 0.00699 -0.0159 0.1208 1.0000
8.250 1.0789 0.01433 0.00730 -0.0150 0.1179 1.0000
8.500 1.1010 0.01462 0.00764 -0.0141 0.1158 1.0000
8.750 1.1233 0.01489 0.00796 -0.0133 0.1139 1.0000
9.000 1.1452 0.01517 0.00828 -0.0124 0.1116 1.0000
9.250 1.1666 0.01548 0.00861 -0.0114 0.1085 1.0000
9.500 1.1872 0.01585 0.00899 -0.0104 0.1047 1.0000
9.750 1.2084 0.01615 0.00934 -0.0094 0.1016 1.0000
10.000 1.2294 0.01646 0.00970 -0.0084 0.0981 1.0000
10.250 1.2495 0.01683 0.01008 -0.0073 0.0944 1.0000
10.500 1.2686 0.01726 0.01053 -0.0061 0.0909 1.0000
10.750 1.2888 0.01759 0.01093 -0.0050 0.0875 1.0000
11.000 1.3077 0.01799 0.01136 -0.0037 0.0828 1.0000
11.250 1.3255 0.01845 0.01184 -0.0024 0.0784 1.0000
11.500 1.3430 0.01891 0.01233 -0.0010 0.0728 1.0000
11.750 1.3586 0.01948 0.01289 0.0007 0.0669 1.0000
12.000 1.3734 0.02008 0.01350 0.0024 0.0618 1.0000
12.250 1.3849 0.02072 0.01417 0.0047 0.0580 1.0000
12.500 1.3960 0.02136 0.01486 0.0069 0.0552 1.0000
12.750 1.4064 0.02214 0.01566 0.0091 0.0521 1.0000
13.000 1.4165 0.02300 0.01658 0.0110 0.0490 1.0000
13.250 1.4285 0.02379 0.01744 0.0127 0.0466 1.0000
13.500 1.4384 0.02477 0.01847 0.0143 0.0437 1.0000
13.750 1.4462 0.02597 0.01971 0.0160 0.0409 1.0000
14.000 1.4579 0.02689 0.02073 0.0173 0.0389 1.0000
14.250 1.4675 0.02802 0.02193 0.0186 0.0360 1.0000
14.750 1.4807 0.03089 0.02492 0.0210 0.0310 1.0000
15.000 1.4856 0.03256 0.02665 0.0221 0.0289 1.0000
15.250 1.4884 0.03448 0.02864 0.0230 0.0271 1.0000
15.500 1.4920 0.03640 0.03066 0.0237 0.0260 1.0000
15.750 1.4941 0.03855 0.03292 0.0242 0.0250 1.0000
16.000 1.4941 0.04101 0.03548 0.0245 0.0241 1.0000
16.250 1.4916 0.04384 0.03843 0.0246 0.0233 1.0000
16.500 1.4863 0.04715 0.04185 0.0243 0.0226 1.0000
16.750 1.4780 0.05104 0.04587 0.0235 0.0219 1.0000
17.000 1.4670 0.05554 0.05050 0.0221 0.0214 1.0000
17.250 1.4557 0.06046 0.05558 0.0203 0.0210 1.0000
17.500 1.4393 0.06647 0.06176 0.0176 0.0207 1.0000
17.750 1.4165 0.07386 0.06933 0.0141 0.0206 1.0000
18.000 1.3863 0.08280 0.07846 0.0098 0.0207 1.0000
18.250 1.3491 0.09299 0.08884 0.0049 0.0209 1.0000
18.500 1.3097 0.10354 0.09956 0.0000 0.0212 1.0000
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Polar data table (+)
Polar graphs
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