BOEING-VERTOL VR-7 AIRFOIL WITH TAB (vr7b-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: BOEING-VERTOL VR-7 AIRFOIL WITH TAB (vr7b-il) Reynolds number: 200,000 Max Cl/Cd: 71.38 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-vr7b-il-200000-n5.txt Download as CSV file: xf-vr7b-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3937 0.10154 0.09854 -0.0007 0.8824 0.0314
-9.500 -0.5303 0.10110 0.09801 0.0019 0.9162 0.0268
-9.250 -0.5319 0.09549 0.09241 -0.0019 0.9078 0.0268
-8.750 -0.5368 0.08396 0.08089 -0.0060 0.8897 0.0214
-8.500 -0.5377 0.07983 0.07676 -0.0086 0.8794 0.0211
-8.250 -0.5431 0.07416 0.07104 -0.0144 0.8677 0.0208
-8.000 -0.5455 0.06839 0.06515 -0.0186 0.8568 0.0203
-7.750 -0.5472 0.06241 0.05898 -0.0218 0.8470 0.0198
-7.500 -0.5459 0.05618 0.05247 -0.0242 0.8369 0.0194
-7.250 -0.5407 0.04992 0.04585 -0.0257 0.8272 0.0190
-7.000 -0.5317 0.04441 0.03990 -0.0260 0.8182 0.0189
-6.750 -0.5171 0.03962 0.03465 -0.0263 0.8081 0.0190
-6.500 -0.4995 0.03596 0.03055 -0.0260 0.7991 0.0195
-6.250 -0.4793 0.03235 0.02637 -0.0256 0.7898 0.0206
-6.000 -0.4568 0.02916 0.02263 -0.0252 0.7811 0.0209
-5.750 -0.4327 0.02660 0.01955 -0.0247 0.7727 0.0212
-5.500 -0.4066 0.02457 0.01705 -0.0244 0.7638 0.0215
-5.250 -0.3810 0.02286 0.01508 -0.0242 0.7554 0.0220
-5.000 -0.3540 0.02182 0.01393 -0.0243 0.7462 0.0227
-4.750 -0.3271 0.02101 0.01295 -0.0242 0.7386 0.0239
-4.500 -0.2991 0.01997 0.01172 -0.0242 0.7307 0.0248
-4.000 -0.2435 0.01799 0.00939 -0.0238 0.7164 0.0260
-3.750 -0.2159 0.01722 0.00846 -0.0236 0.7093 0.0266
-3.500 -0.1880 0.01639 0.00759 -0.0237 0.7015 0.0274
-3.250 -0.1603 0.01583 0.00699 -0.0237 0.6940 0.0289
-3.000 -0.1317 0.01539 0.00649 -0.0239 0.6861 0.0309
-2.750 -0.1032 0.01494 0.00595 -0.0240 0.6790 0.0327
-2.500 -0.0744 0.01444 0.00538 -0.0243 0.6730 0.0345
-2.250 -0.0451 0.01407 0.00496 -0.0246 0.6665 0.0375
-2.000 -0.0161 0.01379 0.00457 -0.0248 0.6607 0.0423
-1.750 0.0136 0.01346 0.00425 -0.0252 0.6544 0.0525
-1.500 0.0431 0.01304 0.00393 -0.0257 0.6484 0.0837
-1.250 0.0697 0.01124 0.00369 -0.0268 0.6435 0.4946
-1.000 0.0969 0.01074 0.00369 -0.0267 0.6372 0.6325
-0.750 0.1199 0.01038 0.00379 -0.0250 0.6311 0.7617
-0.500 0.1401 0.01023 0.00382 -0.0225 0.6259 0.8377
-0.250 0.1621 0.01018 0.00383 -0.0206 0.6195 0.8882
0.000 0.1871 0.01017 0.00375 -0.0195 0.6135 0.9215
0.250 0.2153 0.01015 0.00365 -0.0193 0.6074 0.9444
0.500 0.2493 0.01011 0.00354 -0.0204 0.6004 0.9647
1.000 0.3203 0.01012 0.00340 -0.0238 0.5866 1.0000
1.250 0.3493 0.01020 0.00337 -0.0242 0.5803 1.0000
1.500 0.3790 0.01027 0.00339 -0.0247 0.5731 1.0000
1.750 0.4085 0.01036 0.00340 -0.0252 0.5662 1.0000
2.000 0.4382 0.01045 0.00343 -0.0257 0.5593 1.0000
2.250 0.4679 0.01054 0.00348 -0.0262 0.5519 1.0000
2.500 0.4974 0.01065 0.00353 -0.0267 0.5452 1.0000
2.750 0.5272 0.01076 0.00361 -0.0272 0.5374 1.0000
3.000 0.5566 0.01088 0.00369 -0.0277 0.5304 1.0000
3.250 0.5863 0.01100 0.00380 -0.0282 0.5219 1.0000
3.500 0.6158 0.01114 0.00389 -0.0287 0.5130 1.0000
3.750 0.6452 0.01127 0.00400 -0.0291 0.5032 1.0000
4.000 0.6747 0.01142 0.00414 -0.0296 0.4938 1.0000
4.250 0.7038 0.01159 0.00427 -0.0301 0.4856 1.0000
4.500 0.7332 0.01175 0.00447 -0.0306 0.4761 1.0000
4.750 0.7623 0.01193 0.00463 -0.0310 0.4668 1.0000
5.000 0.7913 0.01213 0.00481 -0.0315 0.4556 1.0000
5.250 0.8204 0.01232 0.00504 -0.0320 0.4445 1.0000
5.500 0.8492 0.01253 0.00526 -0.0324 0.4337 1.0000
5.750 0.8778 0.01276 0.00549 -0.0328 0.4211 1.0000
6.000 0.9063 0.01301 0.00574 -0.0333 0.4077 1.0000
6.250 0.9345 0.01328 0.00602 -0.0337 0.3941 1.0000
6.500 0.9624 0.01361 0.00631 -0.0341 0.3779 1.0000
6.750 0.9901 0.01393 0.00666 -0.0345 0.3631 1.0000
7.000 1.0178 0.01426 0.00704 -0.0348 0.3488 1.0000
7.250 1.0450 0.01464 0.00743 -0.0352 0.3314 1.0000
7.500 1.0717 0.01506 0.00785 -0.0355 0.3107 1.0000
7.750 1.0973 0.01560 0.00835 -0.0358 0.2856 1.0000
8.000 1.1218 0.01628 0.00893 -0.0361 0.2536 1.0000
8.250 1.1441 0.01719 0.00967 -0.0362 0.2145 1.0000
8.500 1.1642 0.01832 0.01060 -0.0363 0.1810 1.0000
8.750 1.1845 0.01933 0.01152 -0.0362 0.1529 1.0000
9.000 1.2032 0.02042 0.01249 -0.0360 0.1274 1.0000
9.250 1.2215 0.02146 0.01348 -0.0356 0.1071 1.0000
9.500 1.2378 0.02261 0.01458 -0.0352 0.0903 1.0000
9.750 1.2530 0.02377 0.01573 -0.0346 0.0795 1.0000
10.000 1.2662 0.02502 0.01700 -0.0340 0.0717 1.0000
10.250 1.2762 0.02625 0.01830 -0.0328 0.0655 1.0000
10.500 1.2842 0.02773 0.01983 -0.0317 0.0604 1.0000
10.750 1.2933 0.02922 0.02141 -0.0309 0.0555 1.0000
11.000 1.2982 0.03117 0.02338 -0.0301 0.0512 1.0000
11.250 1.3078 0.03275 0.02509 -0.0296 0.0472 1.0000
11.500 1.3141 0.03471 0.02713 -0.0292 0.0437 1.0000
11.750 1.3180 0.03698 0.02946 -0.0289 0.0411 1.0000
12.000 1.3236 0.03913 0.03173 -0.0286 0.0388 1.0000
12.250 1.3278 0.04147 0.03416 -0.0285 0.0367 1.0000
12.500 1.3294 0.04412 0.03688 -0.0285 0.0349 1.0000
12.750 1.3296 0.04696 0.03980 -0.0285 0.0335 1.0000
13.000 1.3320 0.04958 0.04255 -0.0285 0.0321 1.0000
13.250 1.3332 0.05237 0.04546 -0.0286 0.0308 1.0000
13.500 1.3335 0.05530 0.04849 -0.0288 0.0298 1.0000
13.750 1.3323 0.05845 0.05173 -0.0291 0.0288 1.0000
14.000 1.3293 0.06191 0.05525 -0.0295 0.0279 1.0000
14.250 1.3263 0.06539 0.05881 -0.0300 0.0271 1.0000
14.500 1.3267 0.06856 0.06213 -0.0304 0.0263 1.0000
14.750 1.3264 0.07190 0.06562 -0.0310 0.0255 1.0000
15.000 1.3254 0.07538 0.06922 -0.0317 0.0247 1.0000
15.250 1.3237 0.07902 0.07297 -0.0326 0.0240 1.0000
15.500 1.3215 0.08283 0.07688 -0.0336 0.0233 1.0000
15.750 1.3183 0.08683 0.08097 -0.0348 0.0227 1.0000
16.000 1.3139 0.09099 0.08519 -0.0360 0.0221 1.0000
16.250 1.3108 0.09502 0.08933 -0.0371 0.0216 1.0000
16.500 1.3081 0.09914 0.09363 -0.0385 0.0211 1.0000
16.750 1.3047 0.10344 0.09808 -0.0399 0.0205 1.0000
17.000 1.3006 0.10788 0.10266 -0.0415 0.0200 1.0000
17.250 1.2961 0.11248 0.10739 -0.0434 0.0195 1.0000
17.500 1.2912 0.11722 0.11226 -0.0454 0.0191 1.0000
17.750 1.2863 0.12208 0.11723 -0.0476 0.0187 1.0000
18.000 1.2812 0.12702 0.12227 -0.0499 0.0183 1.0000
18.250 1.2761 0.13198 0.12733 -0.0524 0.0179 1.0000
18.500 1.2718 0.13671 0.13212 -0.0547 0.0175 1.0000
18.750 1.2646 0.14236 0.13792 -0.0578 0.0172 1.0000
19.000 1.2549 0.14886 0.14461 -0.0615 0.0169 1.0000
19.250 1.2448 0.15563 0.15157 -0.0655 0.0166 1.0000
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Polar data table (+)
Polar graphs
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