BOEING-VERTOL VR-7 AIRFOIL WITH TAB (vr7b-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: BOEING-VERTOL VR-7 AIRFOIL WITH TAB (vr7b-il) Reynolds number: 100,000 Max Cl/Cd: 52.09 at α=8.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-vr7b-il-100000.txt Download as CSV file: xf-vr7b-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: BOEING-VERTOL VR-7 AIRFOIL WITH TAB
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4835 0.11176 0.10754 0.0044 1.0000 0.0934
-9.250 -0.4844 0.10777 0.10360 -0.0005 1.0000 0.0979
-9.000 -0.5063 0.10290 0.09883 -0.0142 1.0000 0.0999
-8.750 -0.4770 0.09870 0.09463 -0.0067 1.0000 0.1033
-8.500 -0.4650 0.09527 0.09121 -0.0077 1.0000 0.1081
-8.250 -0.4762 0.09001 0.08604 -0.0188 1.0000 0.1135
-8.000 -0.4857 0.08316 0.07918 -0.0297 1.0000 0.1159
-7.750 -0.4551 0.08185 0.07794 -0.0216 1.0000 0.1217
-7.500 -0.4828 0.07619 0.07199 -0.0391 1.0000 0.1295
-7.250 -0.4016 0.06109 0.05736 -0.0446 0.9854 0.1456
-7.000 -0.3639 0.05729 0.05363 -0.0445 0.9807 0.1580
-6.750 -0.3461 0.05183 0.04811 -0.0492 0.9720 0.1732
-6.500 -0.4256 0.06111 0.05699 -0.0446 0.9842 0.1639
-6.250 -0.3944 0.05766 0.05352 -0.0481 0.9755 0.1836
-6.000 -0.3678 0.05414 0.04989 -0.0522 0.9656 0.2114
-5.750 -0.3442 0.05142 0.04711 -0.0542 0.9549 0.2417
-5.250 -0.2757 0.03685 0.02968 -0.0637 0.9304 0.0997
-5.000 -0.2494 0.03306 0.02542 -0.0630 0.9200 0.0845
-4.750 -0.2252 0.03060 0.02270 -0.0623 0.9097 0.0803
-4.500 -0.2000 0.02894 0.02069 -0.0617 0.8986 0.0800
-4.250 -0.1742 0.02747 0.01891 -0.0609 0.8888 0.0798
-4.000 -0.1486 0.02612 0.01728 -0.0596 0.8805 0.0787
-3.750 -0.1218 0.02492 0.01591 -0.0590 0.8706 0.0791
-3.500 -0.0970 0.02393 0.01481 -0.0576 0.8625 0.0808
-3.250 -0.0717 0.02320 0.01394 -0.0566 0.8528 0.0853
-3.000 -0.0484 0.02207 0.01294 -0.0554 0.8437 0.0902
-2.750 -0.0259 0.02130 0.01219 -0.0537 0.8355 0.0964
-2.500 -0.0011 0.02058 0.01151 -0.0530 0.8262 0.1091
-2.250 0.0218 0.01968 0.01074 -0.0514 0.8193 0.1432
-2.000 0.0264 0.01712 0.01101 -0.0458 0.8108 0.7611
-1.750 0.0337 0.01724 0.01129 -0.0380 0.8041 0.8786
-1.500 0.0834 0.01749 0.01135 -0.0386 0.7968 0.9677
-1.250 0.1709 0.01729 0.01079 -0.0490 0.7903 1.0000
-1.000 0.1898 0.01723 0.01056 -0.0485 0.7815 1.0000
-0.750 0.2074 0.01715 0.01031 -0.0472 0.7734 1.0000
-0.500 0.2283 0.01726 0.01029 -0.0468 0.7642 1.0000
-0.250 0.2464 0.01723 0.01010 -0.0451 0.7570 1.0000
0.000 0.2689 0.01744 0.01019 -0.0448 0.7474 1.0000
0.250 0.2883 0.01742 0.01002 -0.0430 0.7408 1.0000
0.500 0.3131 0.01771 0.01022 -0.0431 0.7309 1.0000
0.750 0.3349 0.01770 0.01006 -0.0415 0.7249 1.0000
1.000 0.3617 0.01804 0.01033 -0.0420 0.7146 1.0000
1.250 0.3851 0.01803 0.01018 -0.0406 0.7090 1.0000
1.500 0.4129 0.01843 0.01055 -0.0412 0.6983 1.0000
1.750 0.4382 0.01855 0.01056 -0.0404 0.6917 1.0000
2.000 0.4656 0.01889 0.01087 -0.0407 0.6819 1.0000
2.250 0.4920 0.01913 0.01105 -0.0404 0.6743 1.0000
2.500 0.5190 0.01941 0.01131 -0.0404 0.6654 1.0000
2.750 0.5461 0.01976 0.01163 -0.0404 0.6569 1.0000
3.000 0.5729 0.01999 0.01182 -0.0401 0.6488 1.0000
3.250 0.6003 0.02043 0.01229 -0.0404 0.6397 1.0000
3.500 0.6271 0.02059 0.01242 -0.0400 0.6323 1.0000
3.750 0.6545 0.02112 0.01299 -0.0404 0.6226 1.0000
4.000 0.6814 0.02123 0.01308 -0.0398 0.6158 1.0000
4.250 0.7086 0.02176 0.01369 -0.0403 0.6054 1.0000
4.500 0.7355 0.02164 0.01350 -0.0393 0.5988 1.0000
4.750 0.7625 0.02204 0.01399 -0.0396 0.5870 1.0000
5.000 0.7893 0.02224 0.01424 -0.0393 0.5773 1.0000
5.250 0.8167 0.02223 0.01423 -0.0388 0.5693 1.0000
5.500 0.8434 0.02272 0.01484 -0.0391 0.5589 1.0000
5.750 0.8712 0.02245 0.01453 -0.0381 0.5521 1.0000
6.000 0.8978 0.02274 0.01495 -0.0382 0.5398 1.0000
6.250 0.9245 0.02297 0.01528 -0.0380 0.5286 1.0000
6.500 0.9523 0.02282 0.01511 -0.0373 0.5202 1.0000
6.750 0.9792 0.02289 0.01530 -0.0370 0.5082 1.0000
7.000 1.0059 0.02267 0.01512 -0.0364 0.4937 1.0000
7.250 1.0327 0.02230 0.01475 -0.0356 0.4778 1.0000
7.500 1.0593 0.02208 0.01456 -0.0349 0.4616 1.0000
7.750 1.0856 0.02211 0.01466 -0.0345 0.4460 1.0000
8.000 1.1112 0.02221 0.01487 -0.0342 0.4283 1.0000
8.250 1.1357 0.02234 0.01515 -0.0338 0.4073 1.0000
8.500 1.1603 0.02236 0.01513 -0.0332 0.3852 1.0000
8.750 1.1819 0.02269 0.01554 -0.0326 0.3565 1.0000
9.000 1.2011 0.02318 0.01607 -0.0320 0.3217 1.0000
9.250 1.2161 0.02405 0.01683 -0.0311 0.2798 1.0000
9.500 1.2252 0.02558 0.01814 -0.0299 0.2332 1.0000
9.750 1.2287 0.02763 0.01987 -0.0284 0.1950 1.0000
10.000 1.2305 0.02985 0.02187 -0.0267 0.1673 1.0000
10.250 1.2311 0.03195 0.02382 -0.0248 0.1478 1.0000
10.500 1.2330 0.03403 0.02584 -0.0231 0.1319 1.0000
10.750 1.2366 0.03619 0.02793 -0.0216 0.1186 1.0000
11.000 1.2419 0.03833 0.02998 -0.0202 0.1072 1.0000
11.250 1.2500 0.04035 0.03192 -0.0190 0.0977 1.0000
11.500 1.2605 0.04241 0.03409 -0.0177 0.0898 1.0000
11.750 1.2770 0.04440 0.03596 -0.0165 0.0827 1.0000
12.000 1.2861 0.04656 0.03833 -0.0155 0.0775 1.0000
12.250 1.3180 0.04890 0.04050 -0.0148 0.0719 1.0000
12.500 1.3212 0.05140 0.04336 -0.0136 0.0694 1.0000
12.750 1.3262 0.05400 0.04621 -0.0126 0.0665 1.0000
13.000 1.3327 0.05658 0.04893 -0.0119 0.0639 1.0000
13.250 1.3583 0.06034 0.05268 -0.0115 0.0610 1.0000
13.500 1.3494 0.06397 0.05663 -0.0105 0.0603 1.0000
13.750 1.3357 0.06772 0.06073 -0.0099 0.0598 1.0000
14.000 1.3199 0.07197 0.06530 -0.0100 0.0593 1.0000
14.250 1.3018 0.07673 0.07036 -0.0105 0.0589 1.0000
14.500 1.2814 0.08204 0.07596 -0.0118 0.0587 1.0000
14.750 1.2587 0.08797 0.08216 -0.0136 0.0587 1.0000
15.000 1.2340 0.09454 0.08898 -0.0162 0.0589 1.0000
15.250 1.2072 0.10187 0.09654 -0.0196 0.0592 1.0000
15.500 1.1797 0.10996 0.10482 -0.0237 0.0596 1.0000
15.750 1.1521 0.11889 0.11391 -0.0286 0.0602 1.0000
16.000 1.1262 0.12842 0.12357 -0.0339 0.0607 1.0000
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Polar data table (+)
Polar graphs
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