BOEING-VERTOL VR-11X AIRFOIL (vr11x-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: BOEING-VERTOL VR-11X AIRFOIL (vr11x-il) Reynolds number: 1,000,000 Max Cl/Cd: 92.31 at α=8.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-vr11x-il-1000000.txt Download as CSV file: xf-vr11x-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: BOEING-VERTOL VR-11X 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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4850 0.09128 0.08938 -0.0209 0.8802 0.0109
-9.250 -0.4851 0.08700 0.08511 -0.0235 0.8794 0.0109
-9.000 -0.4856 0.08251 0.08063 -0.0269 0.8785 0.0110
-8.750 -0.4899 0.07660 0.07474 -0.0337 0.8776 0.0110
-8.500 -0.4999 0.07051 0.06860 -0.0389 0.8766 0.0111
-8.250 -0.5026 0.06631 0.06435 -0.0407 0.8758 0.0111
-8.000 -0.5005 0.06231 0.06027 -0.0421 0.8750 0.0113
-7.750 -0.4963 0.05837 0.05624 -0.0429 0.8742 0.0114
-7.500 -0.4895 0.05469 0.05245 -0.0433 0.8732 0.0116
-7.250 -0.4812 0.05094 0.04857 -0.0433 0.8721 0.0119
-7.000 -0.4712 0.04715 0.04464 -0.0429 0.8711 0.0123
-6.750 -0.4599 0.04289 0.04015 -0.0419 0.8700 0.0129
-6.500 -0.4454 0.03746 0.03425 -0.0392 0.8689 0.0137
-6.250 -0.4426 0.03169 0.02807 -0.0366 0.8678 0.0139
-6.000 -0.4246 0.02972 0.02599 -0.0358 0.8671 0.0141
-5.750 -0.4045 0.02823 0.02441 -0.0351 0.8666 0.0143
-5.500 -0.3832 0.02690 0.02297 -0.0345 0.8661 0.0146
-5.250 -0.3614 0.02548 0.02141 -0.0337 0.8655 0.0151
-5.000 -0.3394 0.02387 0.01961 -0.0327 0.8645 0.0158
-4.750 -0.3133 0.02328 0.01862 -0.0311 0.8628 0.0171
-4.500 -0.2952 0.01960 0.01466 -0.0295 0.8603 0.0178
-4.250 -0.2705 0.01850 0.01351 -0.0290 0.8575 0.0182
-4.000 -0.2465 0.01360 0.00800 -0.0263 0.8561 0.0116
-3.750 -0.2210 0.01270 0.00700 -0.0256 0.8544 0.0116
-3.500 -0.1959 0.01213 0.00638 -0.0248 0.8519 0.0119
-3.250 -0.1702 0.01167 0.00587 -0.0242 0.8489 0.0124
-3.000 -0.1436 0.01118 0.00536 -0.0238 0.8460 0.0129
-2.750 -0.1172 0.01078 0.00492 -0.0233 0.8429 0.0133
-2.500 -0.0912 0.01045 0.00454 -0.0227 0.8396 0.0136
-2.250 -0.0673 0.00995 0.00398 -0.0216 0.8360 0.0141
-2.000 -0.0404 0.00952 0.00355 -0.0213 0.8323 0.0148
-1.750 -0.0132 0.00924 0.00328 -0.0210 0.8282 0.0158
-1.500 0.0137 0.00899 0.00300 -0.0206 0.8242 0.0170
-1.250 0.0404 0.00865 0.00264 -0.0201 0.8200 0.0190
-1.000 0.0686 0.00841 0.00241 -0.0200 0.8154 0.0214
-0.750 0.0959 0.00812 0.00216 -0.0197 0.8112 0.0330
-0.500 0.1171 0.00716 0.00191 -0.0186 0.8075 0.2588
-0.250 0.1334 0.00591 0.00176 -0.0166 0.8027 0.5872
0.000 0.1497 0.00513 0.00164 -0.0139 0.7965 0.7752
0.250 0.2334 0.00489 0.00196 -0.0259 0.7840 0.9647
0.500 0.2794 0.00516 0.00213 -0.0294 0.7534 0.9803
0.750 0.3185 0.00618 0.00231 -0.0322 0.5694 0.9865
1.000 0.3615 0.00672 0.00250 -0.0359 0.4921 0.9893
1.250 0.3982 0.00727 0.00265 -0.0383 0.4071 0.9917
1.500 0.4317 0.00773 0.00278 -0.0399 0.3390 0.9937
1.750 0.4656 0.00803 0.00288 -0.0416 0.2990 0.9951
2.000 0.5002 0.00833 0.00294 -0.0434 0.2558 0.9962
2.250 0.5342 0.00862 0.00303 -0.0451 0.2173 0.9975
2.500 0.5683 0.00883 0.00311 -0.0467 0.1996 0.9987
2.750 0.6025 0.00899 0.00319 -0.0483 0.1898 0.9998
3.000 0.6296 0.00913 0.00327 -0.0484 0.1836 1.0000
3.250 0.6548 0.00927 0.00338 -0.0480 0.1783 1.0000
3.500 0.6801 0.00936 0.00346 -0.0476 0.1758 1.0000
3.750 0.7052 0.00948 0.00356 -0.0472 0.1726 1.0000
4.000 0.7302 0.00962 0.00366 -0.0468 0.1688 1.0000
4.250 0.7546 0.00983 0.00383 -0.0463 0.1633 1.0000
4.500 0.7796 0.00992 0.00393 -0.0459 0.1614 1.0000
4.750 0.8045 0.01002 0.00403 -0.0454 0.1592 1.0000
5.000 0.8291 0.01015 0.00415 -0.0449 0.1567 1.0000
5.250 0.8534 0.01031 0.00428 -0.0444 0.1537 1.0000
5.500 0.8772 0.01052 0.00447 -0.0438 0.1495 1.0000
5.750 0.9011 0.01070 0.00465 -0.0431 0.1469 1.0000
6.000 0.9255 0.01081 0.00477 -0.0426 0.1454 1.0000
6.250 0.9497 0.01093 0.00492 -0.0420 0.1434 1.0000
6.500 0.9735 0.01108 0.00506 -0.0414 0.1407 1.0000
6.750 0.9970 0.01126 0.00522 -0.0407 0.1376 1.0000
7.000 1.0199 0.01149 0.00545 -0.0399 0.1342 1.0000
7.250 1.0431 0.01167 0.00565 -0.0392 0.1319 1.0000
7.500 1.0668 0.01179 0.00580 -0.0385 0.1298 1.0000
7.750 1.0901 0.01195 0.00597 -0.0378 0.1267 1.0000
8.000 1.1128 0.01215 0.00615 -0.0370 0.1227 1.0000
8.250 1.1349 0.01239 0.00639 -0.0361 0.1187 1.0000
8.500 1.1577 0.01256 0.00659 -0.0353 0.1158 1.0000
8.750 1.1797 0.01278 0.00680 -0.0344 0.1109 1.0000
9.000 1.2010 0.01305 0.00704 -0.0334 0.1048 1.0000
9.250 1.2218 0.01333 0.00730 -0.0324 0.0978 1.0000
9.500 1.2419 0.01366 0.00761 -0.0312 0.0901 1.0000
9.750 1.2606 0.01408 0.00797 -0.0298 0.0807 1.0000
10.000 1.2783 0.01455 0.00839 -0.0283 0.0720 1.0000
10.250 1.2959 0.01501 0.00883 -0.0267 0.0649 1.0000
10.500 1.3129 0.01551 0.00930 -0.0250 0.0578 1.0000
10.750 1.3292 0.01604 0.00981 -0.0233 0.0512 1.0000
11.000 1.3431 0.01664 0.01038 -0.0212 0.0435 1.0000
11.250 1.3523 0.01734 0.01102 -0.0182 0.0330 1.0000
11.500 1.3615 0.01807 0.01171 -0.0153 0.0267 1.0000
11.750 1.3740 0.01864 0.01231 -0.0130 0.0247 1.0000
12.000 1.3871 0.01923 0.01293 -0.0108 0.0236 1.0000
12.250 1.4001 0.01986 0.01360 -0.0088 0.0228 1.0000
12.500 1.4129 0.02053 0.01431 -0.0068 0.0221 1.0000
12.750 1.4254 0.02124 0.01508 -0.0048 0.0215 1.0000
13.000 1.4373 0.02201 0.01592 -0.0029 0.0209 1.0000
13.250 1.4493 0.02278 0.01677 -0.0010 0.0206 1.0000
13.500 1.4616 0.02353 0.01759 0.0007 0.0204 1.0000
13.750 1.4732 0.02435 0.01849 0.0025 0.0201 1.0000
14.000 1.4839 0.02524 0.01946 0.0043 0.0199 1.0000
14.250 1.4937 0.02621 0.02051 0.0061 0.0196 1.0000
14.500 1.5025 0.02727 0.02165 0.0079 0.0194 1.0000
14.750 1.5102 0.02841 0.02288 0.0097 0.0190 1.0000
15.000 1.5169 0.02965 0.02421 0.0115 0.0187 1.0000
15.250 1.5217 0.03106 0.02571 0.0133 0.0184 1.0000
15.500 1.5247 0.03264 0.02737 0.0152 0.0180 1.0000
15.750 1.5255 0.03446 0.02928 0.0170 0.0177 1.0000
16.000 1.5240 0.03655 0.03147 0.0187 0.0174 1.0000
16.250 1.5197 0.03897 0.03401 0.0202 0.0171 1.0000
16.500 1.5124 0.04188 0.03704 0.0215 0.0169 1.0000
16.750 1.5024 0.04533 0.04063 0.0222 0.0167 1.0000
17.000 1.4900 0.04949 0.04494 0.0222 0.0165 1.0000
17.250 1.4860 0.05300 0.04857 0.0216 0.0164 1.0000
17.500 1.4790 0.05718 0.05288 0.0204 0.0164 1.0000
17.750 1.4678 0.06225 0.05808 0.0186 0.0163 1.0000
18.000 1.4508 0.06849 0.06448 0.0160 0.0162 1.0000
18.250 1.4274 0.07612 0.07227 0.0126 0.0162 1.0000
18.500 1.3955 0.08535 0.08168 0.0083 0.0163 1.0000
18.750 1.3587 0.09550 0.09199 0.0037 0.0163 1.0000
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Polar data table (+)
Polar graphs
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