BOEING-VERTOL VR-5 AIRFOIL (vr5-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: BOEING-VERTOL VR-5 AIRFOIL (vr5-il) Reynolds number: 200,000 Max Cl/Cd: 77.99 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-vr5-il-200000-n5.txt Download as CSV file: xf-vr5-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: BOEING-VERTOL VR-5 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.3237 0.09868 0.09537 -0.0181 0.8470 0.0269
-9.750 -0.3270 0.09424 0.09090 -0.0193 0.8413 0.0264
-9.250 -0.4498 0.09256 0.08917 -0.0164 0.8619 0.0195
-9.000 -0.4472 0.08907 0.08566 -0.0177 0.8534 0.0192
-8.750 -0.4460 0.08492 0.08150 -0.0201 0.8443 0.0190
-8.500 -0.4460 0.08007 0.07664 -0.0241 0.8352 0.0187
-8.000 -0.4486 0.06826 0.06468 -0.0367 0.8168 0.0182
-7.750 -0.4460 0.06254 0.05879 -0.0409 0.8091 0.0180
-7.500 -0.4399 0.05692 0.05297 -0.0442 0.8006 0.0179
-7.250 -0.4307 0.05154 0.04731 -0.0463 0.7933 0.0179
-7.000 -0.4183 0.04590 0.04131 -0.0479 0.7856 0.0186
-6.750 -0.4058 0.03846 0.03324 -0.0487 0.7793 0.0194
-6.500 -0.3894 0.03256 0.02669 -0.0488 0.7720 0.0196
-6.250 -0.3693 0.02927 0.02294 -0.0486 0.7654 0.0200
-6.000 -0.3456 0.02755 0.02099 -0.0486 0.7574 0.0205
-5.750 -0.3215 0.02594 0.01908 -0.0484 0.7507 0.0211
-5.500 -0.2961 0.02424 0.01706 -0.0483 0.7431 0.0223
-5.250 -0.2703 0.02231 0.01462 -0.0478 0.7367 0.0242
-5.000 -0.2441 0.02068 0.01268 -0.0476 0.7302 0.0253
-4.750 -0.2176 0.01976 0.01162 -0.0476 0.7237 0.0264
-4.500 -0.1908 0.01889 0.01057 -0.0474 0.7180 0.0279
-4.250 -0.1633 0.01805 0.00954 -0.0473 0.7113 0.0300
-4.000 -0.1366 0.01726 0.00860 -0.0471 0.7056 0.0324
-3.750 -0.1094 0.01672 0.00803 -0.0471 0.6993 0.0348
-3.500 -0.0819 0.01625 0.00747 -0.0471 0.6931 0.0377
-3.000 -0.0278 0.01507 0.00615 -0.0470 0.6825 0.0424
-2.750 -0.0005 0.01461 0.00565 -0.0469 0.6771 0.0444
-2.250 0.0548 0.01392 0.00483 -0.0470 0.6666 0.0493
-2.000 0.0825 0.01357 0.00443 -0.0471 0.6614 0.0523
-1.750 0.1103 0.01331 0.00410 -0.0472 0.6573 0.0561
-1.500 0.1388 0.01311 0.00386 -0.0474 0.6522 0.0614
-1.250 0.1670 0.01287 0.00367 -0.0476 0.6472 0.0763
-1.000 0.1945 0.01246 0.00349 -0.0478 0.6430 0.1523
-0.750 0.2153 0.01078 0.00345 -0.0475 0.6388 0.6255
-0.500 0.2406 0.01062 0.00352 -0.0467 0.6340 0.7058
-0.250 0.2650 0.01053 0.00360 -0.0456 0.6296 0.7726
0.000 0.2882 0.01050 0.00364 -0.0441 0.6259 0.8224
0.250 0.3104 0.01047 0.00374 -0.0423 0.6209 0.8642
0.500 0.3342 0.01048 0.00376 -0.0410 0.6164 0.8938
0.750 0.3613 0.01051 0.00372 -0.0407 0.6125 0.9111
1.000 0.3900 0.01054 0.00371 -0.0408 0.6085 0.9256
1.250 0.4202 0.01057 0.00373 -0.0413 0.6041 0.9398
1.500 0.4526 0.01060 0.00373 -0.0424 0.6003 0.9531
1.750 0.4872 0.01065 0.00371 -0.0438 0.5964 0.9664
2.000 0.5232 0.01069 0.00375 -0.0458 0.5905 0.9817
2.250 0.5577 0.01074 0.00376 -0.0474 0.5845 1.0000
2.500 0.5851 0.01084 0.00380 -0.0475 0.5795 1.0000
2.750 0.6130 0.01095 0.00391 -0.0478 0.5737 1.0000
3.000 0.6408 0.01106 0.00398 -0.0480 0.5686 1.0000
3.250 0.6688 0.01119 0.00409 -0.0483 0.5640 1.0000
3.500 0.6969 0.01132 0.00426 -0.0486 0.5586 1.0000
3.750 0.7249 0.01145 0.00438 -0.0488 0.5535 1.0000
4.000 0.7529 0.01160 0.00453 -0.0490 0.5483 1.0000
4.250 0.7809 0.01174 0.00473 -0.0492 0.5424 1.0000
4.500 0.8088 0.01190 0.00489 -0.0494 0.5372 1.0000
4.750 0.8366 0.01206 0.00511 -0.0496 0.5314 1.0000
5.000 0.8643 0.01221 0.00532 -0.0498 0.5240 1.0000
5.250 0.8918 0.01236 0.00550 -0.0500 0.5161 1.0000
5.500 0.9191 0.01250 0.00570 -0.0501 0.5062 1.0000
5.750 0.9464 0.01264 0.00593 -0.0502 0.4947 1.0000
6.000 0.9733 0.01279 0.00612 -0.0503 0.4806 1.0000
6.250 0.9998 0.01295 0.00634 -0.0503 0.4633 1.0000
6.500 1.0256 0.01315 0.00653 -0.0502 0.4378 1.0000
6.750 1.0495 0.01351 0.00676 -0.0499 0.4008 1.0000
7.000 1.0718 0.01408 0.00716 -0.0495 0.3610 1.0000
7.250 1.0921 0.01487 0.00775 -0.0490 0.3138 1.0000
7.750 1.1268 0.01696 0.00940 -0.0475 0.2296 1.0000
8.000 1.1408 0.01825 0.01040 -0.0466 0.1696 1.0000
8.250 1.1493 0.01994 0.01172 -0.0452 0.1186 1.0000
8.500 1.1617 0.02119 0.01285 -0.0441 0.0905 1.0000
8.750 1.1729 0.02242 0.01398 -0.0428 0.0733 1.0000
9.000 1.1837 0.02359 0.01515 -0.0416 0.0632 1.0000
9.250 1.1953 0.02478 0.01639 -0.0406 0.0554 1.0000
9.500 1.2052 0.02614 0.01779 -0.0395 0.0489 1.0000
9.750 1.2150 0.02755 0.01925 -0.0386 0.0432 1.0000
10.000 1.2236 0.02909 0.02085 -0.0377 0.0390 1.0000
10.250 1.2317 0.03072 0.02253 -0.0369 0.0352 1.0000
10.500 1.2374 0.03262 0.02446 -0.0360 0.0324 1.0000
10.750 1.2450 0.03438 0.02633 -0.0353 0.0300 1.0000
11.000 1.2510 0.03632 0.02836 -0.0347 0.0280 1.0000
11.250 1.2541 0.03858 0.03068 -0.0340 0.0265 1.0000
11.500 1.2572 0.04087 0.03305 -0.0334 0.0255 1.0000
11.750 1.2617 0.04305 0.03536 -0.0328 0.0246 1.0000
12.000 1.2655 0.04531 0.03773 -0.0323 0.0237 1.0000
12.250 1.2688 0.04764 0.04016 -0.0318 0.0230 1.0000
12.500 1.2719 0.05002 0.04264 -0.0313 0.0223 1.0000
12.750 1.2745 0.05247 0.04518 -0.0310 0.0217 1.0000
13.000 1.2763 0.05503 0.04781 -0.0306 0.0211 1.0000
13.250 1.2764 0.05781 0.05065 -0.0303 0.0205 1.0000
13.500 1.2799 0.06029 0.05324 -0.0299 0.0200 1.0000
13.750 1.2838 0.06277 0.05586 -0.0297 0.0195 1.0000
14.000 1.2872 0.06536 0.05858 -0.0296 0.0189 1.0000
14.250 1.2900 0.06803 0.06138 -0.0294 0.0185 1.0000
14.500 1.2923 0.07079 0.06426 -0.0293 0.0181 1.0000
14.750 1.2942 0.07367 0.06726 -0.0294 0.0178 1.0000
15.000 1.2956 0.07667 0.07040 -0.0296 0.0174 1.0000
15.250 1.2963 0.07982 0.07366 -0.0299 0.0171 1.0000
15.500 1.2964 0.08308 0.07702 -0.0304 0.0167 1.0000
15.750 1.2959 0.08645 0.08048 -0.0310 0.0164 1.0000
16.000 1.2945 0.08997 0.08408 -0.0316 0.0161 1.0000
16.250 1.2915 0.09389 0.08816 -0.0325 0.0158 1.0000
16.500 1.2868 0.09825 0.09272 -0.0338 0.0155 1.0000
16.750 1.2810 0.10287 0.09755 -0.0353 0.0153 1.0000
17.000 1.2740 0.10783 0.10271 -0.0370 0.0151 1.0000
17.250 1.2656 0.11316 0.10824 -0.0392 0.0149 1.0000
17.500 1.2560 0.11890 0.11418 -0.0417 0.0148 1.0000
17.750 1.2448 0.12512 0.12059 -0.0447 0.0146 1.0000
18.000 1.2323 0.13185 0.12753 -0.0483 0.0145 1.0000
18.250 1.2180 0.13927 0.13515 -0.0524 0.0145 1.0000
18.500 1.2015 0.14760 0.14368 -0.0574 0.0144 1.0000
18.750 1.1817 0.15727 0.15357 -0.0635 0.0144 1.0000
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