BOEING-VERTOL VR-7 AIRFOIL WITH TAB (vr7b-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: BOEING-VERTOL VR-7 AIRFOIL WITH TAB (vr7b-il) Reynolds number: 100,000 Max Cl/Cd: 53.43 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-vr7b-il-100000-n5.txt Download as CSV file: xf-vr7b-il-100000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4703 0.09874 0.09454 -0.0070 1.0000 0.0573
-8.750 -0.4668 0.09391 0.08975 -0.0111 1.0000 0.0576
-8.500 -0.4954 0.07501 0.07065 -0.0341 0.9736 0.0332
-8.250 -0.4914 0.07029 0.06581 -0.0375 0.9567 0.0330
-8.000 -0.4916 0.06575 0.06109 -0.0397 0.9417 0.0330
-7.750 -0.4906 0.06138 0.05648 -0.0410 0.9277 0.0330
-7.500 -0.4857 0.05722 0.05207 -0.0419 0.9144 0.0330
-7.250 -0.4766 0.05340 0.04802 -0.0422 0.9018 0.0328
-7.000 -0.4654 0.04974 0.04412 -0.0424 0.8899 0.0324
-6.750 -0.4531 0.04613 0.04019 -0.0421 0.8790 0.0321
-6.500 -0.4380 0.04261 0.03628 -0.0418 0.8682 0.0319
-6.250 -0.4202 0.03931 0.03252 -0.0414 0.8578 0.0318
-6.000 -0.4017 0.03642 0.02915 -0.0405 0.8490 0.0320
-5.750 -0.3790 0.03400 0.02606 -0.0399 0.8389 0.0332
-5.500 -0.3574 0.03172 0.02352 -0.0394 0.8301 0.0342
-5.250 -0.3337 0.02983 0.02135 -0.0388 0.8213 0.0346
-5.000 -0.3088 0.02809 0.01930 -0.0382 0.8128 0.0350
-4.750 -0.2839 0.02656 0.01751 -0.0375 0.8048 0.0356
-4.500 -0.2577 0.02519 0.01591 -0.0370 0.7966 0.0364
-4.250 -0.2321 0.02403 0.01456 -0.0362 0.7889 0.0378
-4.000 -0.2053 0.02308 0.01338 -0.0358 0.7809 0.0400
-3.750 -0.1790 0.02216 0.01228 -0.0351 0.7736 0.0415
-3.500 -0.1532 0.02101 0.01115 -0.0347 0.7662 0.0430
-3.250 -0.1272 0.02018 0.01029 -0.0342 0.7586 0.0449
-3.000 -0.1011 0.01949 0.00953 -0.0338 0.7514 0.0476
-2.750 -0.0743 0.01891 0.00885 -0.0335 0.7432 0.0520
-2.500 -0.0477 0.01832 0.00821 -0.0332 0.7353 0.0576
-2.250 -0.0206 0.01778 0.00756 -0.0329 0.7269 0.0655
-2.000 0.0068 0.01715 0.00695 -0.0328 0.7189 0.0861
-1.750 0.0286 0.01495 0.00655 -0.0327 0.7118 0.4800
-1.500 0.0457 0.01421 0.00666 -0.0294 0.7056 0.7086
-1.250 0.0622 0.01406 0.00679 -0.0253 0.6983 0.8302
-1.000 0.0818 0.01402 0.00674 -0.0217 0.6927 0.9146
-0.750 0.1217 0.01398 0.00656 -0.0234 0.6847 0.9618
-0.500 0.1663 0.01394 0.00629 -0.0267 0.6780 0.9844
-0.250 0.2080 0.01395 0.00613 -0.0298 0.6705 1.0000
0.000 0.2319 0.01399 0.00600 -0.0294 0.6635 1.0000
0.250 0.2568 0.01406 0.00590 -0.0291 0.6569 1.0000
0.500 0.2835 0.01416 0.00588 -0.0292 0.6492 1.0000
0.750 0.3095 0.01425 0.00580 -0.0289 0.6434 1.0000
1.000 0.3380 0.01440 0.00588 -0.0294 0.6350 1.0000
1.250 0.3652 0.01451 0.00586 -0.0294 0.6285 1.0000
1.500 0.3938 0.01467 0.00596 -0.0298 0.6207 1.0000
1.750 0.4218 0.01480 0.00600 -0.0299 0.6137 1.0000
2.000 0.4503 0.01496 0.00610 -0.0303 0.6063 1.0000
2.250 0.4788 0.01512 0.00622 -0.0305 0.5987 1.0000
2.500 0.5071 0.01528 0.00632 -0.0308 0.5917 1.0000
2.750 0.5359 0.01546 0.00649 -0.0312 0.5837 1.0000
3.000 0.5641 0.01561 0.00660 -0.0313 0.5770 1.0000
3.250 0.5929 0.01581 0.00682 -0.0318 0.5685 1.0000
3.500 0.6211 0.01597 0.00693 -0.0319 0.5619 1.0000
3.750 0.6499 0.01619 0.00720 -0.0323 0.5532 1.0000
4.000 0.6780 0.01635 0.00733 -0.0324 0.5464 1.0000
4.250 0.7065 0.01658 0.00763 -0.0328 0.5373 1.0000
4.500 0.7346 0.01675 0.00781 -0.0330 0.5288 1.0000
4.750 0.7627 0.01693 0.00801 -0.0332 0.5190 1.0000
5.000 0.7908 0.01715 0.00829 -0.0335 0.5090 1.0000
5.250 0.8185 0.01732 0.00845 -0.0335 0.5009 1.0000
5.500 0.8464 0.01759 0.00882 -0.0338 0.4898 1.0000
5.750 0.8740 0.01782 0.00910 -0.0340 0.4793 1.0000
6.000 0.9014 0.01801 0.00929 -0.0340 0.4696 1.0000
6.250 0.9288 0.01833 0.00975 -0.0343 0.4580 1.0000
6.500 0.9559 0.01863 0.01013 -0.0344 0.4469 1.0000
6.750 0.9827 0.01890 0.01047 -0.0345 0.4344 1.0000
7.000 1.0089 0.01917 0.01083 -0.0345 0.4175 1.0000
7.250 1.0344 0.01947 0.01116 -0.0345 0.3982 1.0000
7.500 1.0593 0.01983 0.01151 -0.0344 0.3788 1.0000
7.750 1.0841 0.02029 0.01204 -0.0343 0.3619 1.0000
8.000 1.1083 0.02080 0.01265 -0.0343 0.3439 1.0000
8.250 1.1316 0.02137 0.01331 -0.0342 0.3219 1.0000
8.500 1.1531 0.02205 0.01402 -0.0340 0.2961 1.0000
8.750 1.1724 0.02291 0.01483 -0.0336 0.2656 1.0000
9.000 1.1888 0.02401 0.01583 -0.0331 0.2319 1.0000
9.250 1.2017 0.02539 0.01706 -0.0323 0.1993 1.0000
9.500 1.2118 0.02695 0.01850 -0.0314 0.1732 1.0000
9.750 1.2204 0.02858 0.02009 -0.0305 0.1497 1.0000
10.000 1.2247 0.03034 0.02180 -0.0292 0.1308 1.0000
10.250 1.2276 0.03224 0.02368 -0.0280 0.1162 1.0000
10.500 1.2309 0.03427 0.02572 -0.0270 0.1039 1.0000
10.750 1.2332 0.03650 0.02796 -0.0263 0.0945 1.0000
11.000 1.2340 0.03897 0.03043 -0.0258 0.0869 1.0000
11.250 1.2366 0.04135 0.03290 -0.0253 0.0803 1.0000
11.500 1.2364 0.04409 0.03569 -0.0251 0.0750 1.0000
11.750 1.2377 0.04673 0.03841 -0.0248 0.0701 1.0000
12.000 1.2389 0.04943 0.04122 -0.0247 0.0655 1.0000
12.250 1.2366 0.05251 0.04431 -0.0246 0.0622 1.0000
12.500 1.2390 0.05512 0.04705 -0.0243 0.0590 1.0000
12.750 1.2407 0.05784 0.04989 -0.0242 0.0559 1.0000
13.000 1.2408 0.06077 0.05288 -0.0242 0.0533 1.0000
13.250 1.2400 0.06371 0.05580 -0.0240 0.0510 1.0000
13.500 1.2432 0.06642 0.05874 -0.0240 0.0486 1.0000
13.750 1.2451 0.06930 0.06177 -0.0240 0.0463 1.0000
14.000 1.2466 0.07224 0.06482 -0.0242 0.0445 1.0000
14.250 1.2477 0.07524 0.06789 -0.0244 0.0431 1.0000
14.500 1.2496 0.07810 0.07076 -0.0244 0.0416 1.0000
14.750 1.2498 0.08155 0.07446 -0.0249 0.0402 1.0000
15.000 1.2486 0.08522 0.07833 -0.0257 0.0388 1.0000
15.250 1.2465 0.08906 0.08235 -0.0266 0.0375 1.0000
15.500 1.2444 0.09296 0.08638 -0.0277 0.0364 1.0000
15.750 1.2425 0.09683 0.09036 -0.0289 0.0355 1.0000
16.000 1.2413 0.10057 0.09419 -0.0300 0.0347 1.0000
16.250 1.2395 0.10444 0.09813 -0.0310 0.0338 1.0000
16.500 1.2289 0.11035 0.10432 -0.0337 0.0332 1.0000
16.750 1.2165 0.11679 0.11102 -0.0368 0.0327 1.0000
17.000 1.2021 0.12387 0.11834 -0.0406 0.0322 1.0000
17.250 1.1853 0.13175 0.12645 -0.0450 0.0319 1.0000
17.500 1.1651 0.14088 0.13580 -0.0505 0.0317 1.0000
17.750 1.1376 0.15255 0.14768 -0.0578 0.0319 1.0000
18.000 1.0903 0.17143 0.16674 -0.0698 0.0327 1.0000
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Polar data table (+)
Polar graphs
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