BOEING-VERTOL VR-7 AIRFOIL (vr7-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: BOEING-VERTOL VR-7 AIRFOIL (vr7-il) Reynolds number: 200,000 Max Cl/Cd: 72.35 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-vr7-il-200000-n5.txt Download as CSV file: xf-vr7-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: BOEING-VERTOL VR-7 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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.3219 0.08938 0.08610 -0.0377 1.0000 0.0310
-10.000 -0.3239 0.08462 0.08137 -0.0393 1.0000 0.0310
-9.500 -0.4162 0.08020 0.07672 -0.0408 1.0000 0.0202
-9.250 -0.4182 0.07625 0.07282 -0.0427 1.0000 0.0200
-9.000 -0.4241 0.07150 0.06813 -0.0459 1.0000 0.0198
-8.750 -0.4377 0.06635 0.06301 -0.0500 1.0000 0.0196
-8.500 -0.4535 0.06247 0.05911 -0.0501 1.0000 0.0194
-8.250 -0.4573 0.05705 0.05357 -0.0530 0.9847 0.0191
-8.000 -0.4475 0.04996 0.04614 -0.0585 0.9468 0.0189
-7.750 -0.4328 0.04381 0.03955 -0.0621 0.9148 0.0189
-7.500 -0.4222 0.03787 0.03295 -0.0629 0.8840 0.0197
-7.250 -0.4111 0.03329 0.02764 -0.0619 0.8574 0.0202
-7.000 -0.3956 0.03034 0.02414 -0.0607 0.8354 0.0203
-6.750 -0.3782 0.02801 0.02146 -0.0596 0.8172 0.0205
-6.500 -0.3585 0.02628 0.01942 -0.0586 0.8016 0.0209
-6.250 -0.3373 0.02484 0.01772 -0.0577 0.7881 0.0212
-6.000 -0.3150 0.02362 0.01625 -0.0569 0.7763 0.0218
-5.750 -0.2919 0.02256 0.01492 -0.0561 0.7659 0.0228
-5.500 -0.2681 0.02137 0.01344 -0.0553 0.7558 0.0237
-5.250 -0.2436 0.02016 0.01193 -0.0545 0.7472 0.0242
-5.000 -0.2185 0.01911 0.01064 -0.0538 0.7392 0.0247
-4.750 -0.1932 0.01820 0.00955 -0.0532 0.7319 0.0252
-4.500 -0.1686 0.01730 0.00860 -0.0526 0.7243 0.0258
-4.250 -0.1438 0.01666 0.00790 -0.0520 0.7174 0.0267
-4.000 -0.1187 0.01618 0.00737 -0.0515 0.7095 0.0282
-3.750 -0.0937 0.01571 0.00679 -0.0508 0.7025 0.0299
-3.500 -0.0689 0.01520 0.00621 -0.0502 0.6944 0.0309
-3.250 -0.0451 0.01465 0.00561 -0.0494 0.6875 0.0323
-3.000 -0.0202 0.01426 0.00519 -0.0488 0.6800 0.0341
-2.750 0.0052 0.01395 0.00478 -0.0482 0.6740 0.0368
-2.500 0.0306 0.01363 0.00442 -0.0478 0.6677 0.0415
-2.250 0.0564 0.01336 0.00409 -0.0473 0.6615 0.0487
-2.000 0.0819 0.01307 0.00379 -0.0467 0.6566 0.0664
-1.750 0.1029 0.01212 0.00352 -0.0459 0.6504 0.2304
-1.500 0.1185 0.01095 0.00345 -0.0440 0.6448 0.5306
-1.250 0.1403 0.01062 0.00344 -0.0425 0.6395 0.6338
-1.000 0.1622 0.01031 0.00348 -0.0408 0.6331 0.7269
-0.750 0.1874 0.01012 0.00353 -0.0396 0.6276 0.8110
-0.500 0.2219 0.01010 0.00358 -0.0403 0.6217 0.8722
-0.250 0.2602 0.01014 0.00358 -0.0421 0.6148 0.9064
0.000 0.3002 0.01022 0.00355 -0.0444 0.6089 0.9298
0.250 0.3384 0.01027 0.00355 -0.0465 0.6015 0.9460
0.500 0.3748 0.01033 0.00351 -0.0483 0.5949 0.9589
0.750 0.4110 0.01039 0.00351 -0.0500 0.5878 0.9705
1.000 0.4492 0.01044 0.00348 -0.0523 0.5807 0.9794
1.250 0.4864 0.01049 0.00348 -0.0543 0.5735 0.9882
1.500 0.5238 0.01054 0.00347 -0.0565 0.5660 0.9963
1.750 0.5550 0.01060 0.00348 -0.0573 0.5590 1.0000
2.000 0.5781 0.01067 0.00352 -0.0565 0.5519 1.0000
2.250 0.6013 0.01076 0.00356 -0.0556 0.5452 1.0000
2.500 0.6248 0.01086 0.00364 -0.0548 0.5373 1.0000
2.750 0.6482 0.01096 0.00370 -0.0540 0.5299 1.0000
3.000 0.6718 0.01107 0.00379 -0.0532 0.5213 1.0000
3.250 0.6954 0.01119 0.00389 -0.0524 0.5127 1.0000
3.500 0.7190 0.01133 0.00400 -0.0516 0.5043 1.0000
3.750 0.7427 0.01146 0.00413 -0.0508 0.4957 1.0000
4.000 0.7662 0.01162 0.00426 -0.0500 0.4869 1.0000
4.250 0.7897 0.01177 0.00441 -0.0492 0.4761 1.0000
4.500 0.8131 0.01194 0.00457 -0.0483 0.4666 1.0000
4.750 0.8365 0.01212 0.00476 -0.0475 0.4577 1.0000
5.000 0.8601 0.01231 0.00497 -0.0468 0.4484 1.0000
5.250 0.8832 0.01251 0.00516 -0.0459 0.4388 1.0000
5.500 0.9063 0.01271 0.00538 -0.0451 0.4270 1.0000
5.750 0.9291 0.01293 0.00562 -0.0442 0.4145 1.0000
6.000 0.9514 0.01317 0.00585 -0.0433 0.4007 1.0000
6.250 0.9731 0.01345 0.00610 -0.0422 0.3857 1.0000
6.500 0.9947 0.01375 0.00640 -0.0412 0.3708 1.0000
6.750 1.0164 0.01406 0.00673 -0.0402 0.3567 1.0000
7.000 1.0380 0.01437 0.00707 -0.0392 0.3427 1.0000
7.250 1.0593 0.01471 0.00743 -0.0382 0.3276 1.0000
7.500 1.0793 0.01510 0.00782 -0.0370 0.3089 1.0000
7.750 1.0975 0.01558 0.00825 -0.0356 0.2854 1.0000
8.000 1.1136 0.01618 0.00875 -0.0339 0.2572 1.0000
8.250 1.1276 0.01691 0.00935 -0.0320 0.2256 1.0000
8.500 1.1387 0.01779 0.01008 -0.0298 0.1939 1.0000
8.750 1.1493 0.01869 0.01086 -0.0275 0.1705 1.0000
9.000 1.1599 0.01955 0.01165 -0.0252 0.1469 1.0000
9.250 1.1681 0.02046 0.01247 -0.0227 0.1275 1.0000
9.500 1.1745 0.02134 0.01333 -0.0198 0.1118 1.0000
9.750 1.1798 0.02233 0.01427 -0.0170 0.0971 1.0000
10.000 1.1849 0.02341 0.01533 -0.0145 0.0866 1.0000
10.250 1.1902 0.02458 0.01651 -0.0123 0.0787 1.0000
10.500 1.1955 0.02585 0.01780 -0.0103 0.0718 1.0000
10.750 1.2010 0.02720 0.01921 -0.0087 0.0666 1.0000
11.000 1.2061 0.02869 0.02077 -0.0073 0.0616 1.0000
11.250 1.2091 0.03044 0.02255 -0.0060 0.0576 1.0000
11.500 1.2151 0.03204 0.02427 -0.0050 0.0535 1.0000
11.750 1.2176 0.03402 0.02629 -0.0041 0.0497 1.0000
12.000 1.2210 0.03601 0.02836 -0.0034 0.0464 1.0000
12.250 1.2254 0.03796 0.03041 -0.0028 0.0433 1.0000
12.500 1.2268 0.04026 0.03276 -0.0023 0.0406 1.0000
12.750 1.2273 0.04268 0.03527 -0.0019 0.0387 1.0000
13.000 1.2296 0.04499 0.03769 -0.0016 0.0369 1.0000
13.250 1.2310 0.04745 0.04024 -0.0014 0.0352 1.0000
13.500 1.2306 0.05014 0.04299 -0.0014 0.0338 1.0000
13.750 1.2272 0.05323 0.04612 -0.0015 0.0324 1.0000
14.000 1.2275 0.05598 0.04899 -0.0016 0.0313 1.0000
14.250 1.2281 0.05879 0.05192 -0.0018 0.0302 1.0000
14.500 1.2279 0.06177 0.05501 -0.0021 0.0291 1.0000
14.750 1.2274 0.06488 0.05822 -0.0026 0.0282 1.0000
15.000 1.2263 0.06814 0.06158 -0.0033 0.0274 1.0000
15.250 1.2234 0.07171 0.06521 -0.0041 0.0265 1.0000
15.500 1.2207 0.07527 0.06884 -0.0049 0.0259 1.0000
15.750 1.2210 0.07856 0.07227 -0.0057 0.0251 1.0000
16.000 1.2206 0.08201 0.07586 -0.0067 0.0243 1.0000
16.250 1.2193 0.08565 0.07963 -0.0077 0.0236 1.0000
16.500 1.2175 0.08945 0.08354 -0.0090 0.0229 1.0000
16.750 1.2152 0.09334 0.08753 -0.0104 0.0224 1.0000
17.000 1.2119 0.09751 0.09179 -0.0120 0.0217 1.0000
17.250 1.2085 0.10170 0.09605 -0.0137 0.0212 1.0000
17.500 1.2061 0.10565 0.10006 -0.0151 0.0208 1.0000
17.750 1.2018 0.11025 0.10487 -0.0171 0.0203 1.0000
18.000 1.1976 0.11485 0.10963 -0.0192 0.0198 1.0000
18.250 1.1927 0.11965 0.11458 -0.0214 0.0194 1.0000
18.500 1.1875 0.12456 0.11964 -0.0238 0.0190 1.0000
18.750 1.1812 0.12984 0.12505 -0.0266 0.0185 1.0000
19.000 1.1750 0.13514 0.13047 -0.0294 0.0181 1.0000
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Polar data table (+)
Polar graphs
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