BOEING-VERTOL VR-1 AIRFOIL (vr1-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: BOEING-VERTOL VR-1 AIRFOIL (vr1-il) Reynolds number: 200,000 Max Cl/Cd: 53.58 at α=3° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-vr1-il-200000-n5.txt Download as CSV file: xf-vr1-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: BOEING-VERTOL VR-1 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
------ -------- --------- --------- -------- -------- --------
-11.000 -0.5609 0.08264 0.07858 -0.0432 1.0000 0.0249
-10.750 -0.5683 0.07658 0.07255 -0.0467 1.0000 0.0244
-10.500 -0.6128 0.06265 0.05847 -0.0581 1.0000 0.0238
-10.250 -0.6449 0.05676 0.05242 -0.0604 1.0000 0.0238
-10.000 -0.6714 0.05315 0.04866 -0.0584 1.0000 0.0236
-9.750 -0.6943 0.05006 0.04540 -0.0546 1.0000 0.0236
-9.500 -0.7101 0.04688 0.04200 -0.0511 1.0000 0.0235
-9.250 -0.7215 0.04393 0.03882 -0.0475 1.0000 0.0235
-9.000 -0.7305 0.04118 0.03580 -0.0434 1.0000 0.0234
-8.750 -0.7366 0.03876 0.03312 -0.0393 1.0000 0.0233
-8.500 -0.7241 0.03568 0.02966 -0.0387 0.9959 0.0233
-8.250 -0.7026 0.03276 0.02631 -0.0395 0.9898 0.0233
-8.000 -0.6774 0.03027 0.02343 -0.0404 0.9847 0.0235
-7.750 -0.6524 0.02827 0.02110 -0.0408 0.9789 0.0236
-7.500 -0.6245 0.02648 0.01902 -0.0416 0.9740 0.0238
-7.250 -0.5936 0.02487 0.01713 -0.0428 0.9707 0.0241
-7.000 -0.5666 0.02364 0.01568 -0.0430 0.9645 0.0246
-6.750 -0.5358 0.02253 0.01433 -0.0439 0.9600 0.0252
-6.500 -0.5036 0.02130 0.01298 -0.0452 0.9565 0.0256
-6.250 -0.4753 0.02023 0.01188 -0.0456 0.9507 0.0260
-6.000 -0.4457 0.01928 0.01090 -0.0462 0.9453 0.0263
-5.750 -0.4140 0.01840 0.00999 -0.0472 0.9412 0.0268
-5.500 -0.3868 0.01767 0.00924 -0.0473 0.9343 0.0272
-5.250 -0.3582 0.01697 0.00851 -0.0476 0.9283 0.0278
-5.000 -0.3280 0.01632 0.00782 -0.0482 0.9235 0.0283
-4.750 -0.3035 0.01581 0.00728 -0.0477 0.9152 0.0291
-4.500 -0.2749 0.01528 0.00671 -0.0479 0.9095 0.0303
-4.250 -0.2497 0.01481 0.00623 -0.0475 0.9022 0.0315
-4.000 -0.2232 0.01440 0.00579 -0.0473 0.8953 0.0327
-3.750 -0.1953 0.01404 0.00536 -0.0472 0.8895 0.0339
-3.500 -0.1705 0.01375 0.00503 -0.0466 0.8816 0.0354
-3.250 -0.1433 0.01341 0.00466 -0.0464 0.8757 0.0379
-3.000 -0.1182 0.01313 0.00439 -0.0458 0.8684 0.0434
-2.500 -0.0724 0.01182 0.00379 -0.0442 0.8552 0.2016
-2.250 -0.0549 0.01093 0.00363 -0.0426 0.8472 0.3679
-2.000 -0.0329 0.01041 0.00350 -0.0415 0.8413 0.4770
-1.750 -0.0129 0.01001 0.00350 -0.0398 0.8339 0.5743
-1.500 0.0097 0.00974 0.00351 -0.0383 0.8275 0.6576
-1.250 0.0341 0.00957 0.00356 -0.0371 0.8218 0.7238
-1.000 0.0586 0.00951 0.00365 -0.0359 0.8148 0.7753
-0.750 0.0853 0.00950 0.00374 -0.0350 0.8092 0.8230
-0.500 0.1136 0.00954 0.00383 -0.0345 0.8032 0.8527
-0.250 0.1425 0.00958 0.00386 -0.0344 0.7966 0.8683
0.000 0.1734 0.00962 0.00387 -0.0347 0.7913 0.8822
0.250 0.2031 0.00968 0.00394 -0.0348 0.7844 0.8959
0.500 0.2329 0.00973 0.00397 -0.0350 0.7780 0.9089
0.750 0.2674 0.00980 0.00401 -0.0361 0.7722 0.9178
1.000 0.2982 0.00985 0.00407 -0.0365 0.7636 0.9279
1.250 0.3310 0.00987 0.00407 -0.0373 0.7523 0.9368
1.500 0.3644 0.00989 0.00404 -0.0381 0.7381 0.9450
1.750 0.3974 0.00992 0.00404 -0.0389 0.7223 0.9537
2.000 0.4333 0.00995 0.00403 -0.0403 0.7019 0.9604
2.250 0.4671 0.00999 0.00398 -0.0413 0.6731 0.9675
2.500 0.5015 0.01008 0.00394 -0.0424 0.6341 0.9744
2.750 0.5349 0.01024 0.00393 -0.0435 0.5881 0.9814
3.000 0.5658 0.01056 0.00394 -0.0442 0.5137 0.9875
3.250 0.5885 0.01150 0.00415 -0.0437 0.3675 0.9947
3.500 0.6075 0.01280 0.00464 -0.0431 0.2122 1.0000
3.750 0.6182 0.01351 0.00502 -0.0403 0.1475 1.0000
4.000 0.6322 0.01401 0.00534 -0.0379 0.1189 1.0000
4.250 0.6477 0.01443 0.00565 -0.0357 0.1031 1.0000
4.500 0.6641 0.01480 0.00598 -0.0337 0.0914 1.0000
4.750 0.6811 0.01516 0.00632 -0.0317 0.0821 1.0000
5.000 0.6977 0.01556 0.00668 -0.0297 0.0747 1.0000
5.250 0.7151 0.01595 0.00705 -0.0278 0.0683 1.0000
5.500 0.7319 0.01639 0.00746 -0.0259 0.0628 1.0000
5.750 0.7493 0.01680 0.00789 -0.0240 0.0581 1.0000
6.000 0.7656 0.01732 0.00836 -0.0220 0.0544 1.0000
6.250 0.7831 0.01778 0.00886 -0.0202 0.0514 1.0000
6.500 0.8003 0.01829 0.00938 -0.0184 0.0489 1.0000
6.750 0.8165 0.01890 0.00996 -0.0165 0.0468 1.0000
7.000 0.8334 0.01950 0.01059 -0.0147 0.0450 1.0000
7.250 0.8511 0.02007 0.01120 -0.0130 0.0431 1.0000
7.500 0.8686 0.02066 0.01182 -0.0114 0.0415 1.0000
7.750 0.8857 0.02130 0.01246 -0.0098 0.0401 1.0000
8.000 0.9014 0.02215 0.01328 -0.0080 0.0390 1.0000
8.250 0.9195 0.02288 0.01410 -0.0066 0.0382 1.0000
8.500 0.9374 0.02369 0.01499 -0.0051 0.0373 1.0000
8.750 0.9552 0.02452 0.01589 -0.0037 0.0363 1.0000
9.000 0.9726 0.02534 0.01677 -0.0023 0.0354 1.0000
9.250 0.9894 0.02614 0.01762 -0.0008 0.0346 1.0000
9.500 1.0055 0.02696 0.01846 0.0007 0.0338 1.0000
9.750 1.0224 0.02801 0.01952 0.0019 0.0330 1.0000
10.000 1.0400 0.02913 0.02078 0.0031 0.0325 1.0000
10.250 1.0569 0.03034 0.02215 0.0044 0.0319 1.0000
10.500 1.0726 0.03162 0.02360 0.0058 0.0314 1.0000
10.750 1.0868 0.03297 0.02513 0.0073 0.0309 1.0000
11.000 1.0991 0.03440 0.02674 0.0090 0.0304 1.0000
11.250 1.1097 0.03588 0.02839 0.0107 0.0300 1.0000
11.500 1.1183 0.03731 0.02998 0.0126 0.0295 1.0000
11.750 1.1255 0.03871 0.03152 0.0145 0.0291 1.0000
12.000 1.1317 0.04020 0.03312 0.0163 0.0287 1.0000
12.250 1.1377 0.04166 0.03469 0.0180 0.0283 1.0000
12.500 1.1427 0.04329 0.03640 0.0195 0.0280 1.0000
12.750 1.1455 0.04536 0.03858 0.0210 0.0277 1.0000
13.000 1.1390 0.04806 0.04156 0.0228 0.0276 1.0000
13.250 1.1285 0.05119 0.04498 0.0244 0.0274 1.0000
13.500 1.1144 0.05482 0.04891 0.0254 0.0272 1.0000
13.750 1.0979 0.05896 0.05332 0.0257 0.0271 1.0000
14.000 1.0778 0.06379 0.05841 0.0252 0.0271 1.0000
14.250 1.0525 0.06971 0.06459 0.0236 0.0270 1.0000
14.500 1.0242 0.07676 0.07189 0.0205 0.0270 1.0000
14.750 0.9913 0.08552 0.08088 0.0156 0.0271 1.0000
15.000 0.9420 0.09949 0.09511 0.0063 0.0273 1.0000
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