BOEING-VERTOL VR-14 AIRFOIL (vr14-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: BOEING-VERTOL VR-14 AIRFOIL (vr14-il) Reynolds number: 100,000 Max Cl/Cd: 40.32 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-vr14-il-100000-n5.txt Download as CSV file: xf-vr14-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: BOEING-VERTOL VR-14 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.5515 0.11757 0.11267 0.0084 1.0000 0.0370
-9.500 -0.5509 0.11373 0.10887 0.0044 1.0000 0.0374
-9.250 -0.5492 0.10968 0.10486 0.0009 1.0000 0.0376
-9.000 -0.5482 0.10541 0.10064 -0.0032 1.0000 0.0377
-8.750 -0.5472 0.10087 0.09613 -0.0076 1.0000 0.0378
-8.500 -0.5469 0.09626 0.09153 -0.0120 1.0000 0.0379
-8.250 -0.5454 0.09187 0.08712 -0.0151 1.0000 0.0379
-8.000 -0.5420 0.08744 0.08263 -0.0177 1.0000 0.0380
-7.750 -0.5358 0.08344 0.07884 -0.0113 1.0000 0.0407
-7.500 -0.5313 0.07922 0.07461 -0.0139 1.0000 0.0414
-7.250 -0.5262 0.07462 0.06997 -0.0168 1.0000 0.0415
-7.000 -0.5188 0.06650 0.06158 -0.0212 1.0000 0.0264
-6.750 -0.5114 0.06234 0.05735 -0.0219 1.0000 0.0255
-6.500 -0.5023 0.05792 0.05279 -0.0226 1.0000 0.0246
-6.250 -0.4920 0.05340 0.04807 -0.0230 1.0000 0.0237
-6.000 -0.4805 0.04897 0.04338 -0.0227 1.0000 0.0230
-5.750 -0.4683 0.04473 0.03884 -0.0218 1.0000 0.0225
-5.500 -0.4558 0.04088 0.03461 -0.0203 1.0000 0.0223
-5.250 -0.4433 0.03754 0.03093 -0.0183 1.0000 0.0224
-5.000 -0.4305 0.03463 0.02766 -0.0159 1.0000 0.0226
-4.750 -0.4164 0.03223 0.02491 -0.0137 1.0000 0.0238
-4.500 -0.4007 0.03002 0.02222 -0.0112 1.0000 0.0262
-4.250 -0.3836 0.02794 0.01959 -0.0088 1.0000 0.0278
-4.000 -0.3666 0.02566 0.01708 -0.0071 1.0000 0.0291
-3.750 -0.3483 0.02456 0.01587 -0.0057 1.0000 0.0321
-3.500 -0.3189 0.02305 0.01395 -0.0058 0.9970 0.0360
-3.250 -0.2845 0.02127 0.01185 -0.0067 0.9931 0.0391
-3.000 -0.2514 0.02005 0.01060 -0.0081 0.9881 0.0442
-2.750 -0.2161 0.01895 0.00935 -0.0094 0.9840 0.0480
-2.500 -0.1834 0.01797 0.00833 -0.0105 0.9787 0.0534
-2.250 -0.1496 0.01719 0.00754 -0.0118 0.9736 0.0578
-2.000 -0.1141 0.01662 0.00689 -0.0134 0.9690 0.0656
-1.750 -0.0819 0.01611 0.00635 -0.0144 0.9626 0.0736
-1.500 -0.0466 0.01563 0.00586 -0.0159 0.9577 0.0916
-1.250 0.0448 0.01262 0.00597 -0.0275 0.9758 1.0000
-1.000 0.0866 0.01260 0.00571 -0.0305 0.9658 1.0000
-0.750 0.1298 0.01252 0.00543 -0.0334 0.9493 1.0000
-0.500 0.1667 0.01241 0.00516 -0.0347 0.9286 1.0000
-0.250 0.1929 0.01235 0.00497 -0.0339 0.9063 1.0000
0.000 0.2178 0.01230 0.00480 -0.0327 0.8873 1.0000
0.250 0.2412 0.01227 0.00468 -0.0314 0.8695 1.0000
0.500 0.2642 0.01226 0.00460 -0.0301 0.8516 1.0000
0.750 0.2871 0.01225 0.00450 -0.0286 0.8330 1.0000
1.000 0.3099 0.01223 0.00440 -0.0271 0.8136 1.0000
1.250 0.3329 0.01222 0.00433 -0.0257 0.7914 1.0000
1.500 0.3557 0.01222 0.00426 -0.0241 0.7674 1.0000
1.750 0.3787 0.01225 0.00419 -0.0226 0.7389 1.0000
2.000 0.4017 0.01229 0.00414 -0.0212 0.7026 1.0000
2.250 0.4244 0.01238 0.00407 -0.0196 0.6530 1.0000
2.500 0.4464 0.01258 0.00397 -0.0179 0.5790 1.0000
2.750 0.4674 0.01307 0.00396 -0.0162 0.4851 1.0000
3.000 0.4892 0.01368 0.00413 -0.0151 0.4100 1.0000
3.250 0.5119 0.01425 0.00439 -0.0143 0.3582 1.0000
3.500 0.5351 0.01476 0.00468 -0.0136 0.3247 1.0000
3.750 0.5586 0.01522 0.00504 -0.0129 0.3003 1.0000
4.000 0.5821 0.01567 0.00538 -0.0122 0.2811 1.0000
4.250 0.6058 0.01611 0.00574 -0.0115 0.2650 1.0000
4.500 0.6294 0.01656 0.00613 -0.0109 0.2519 1.0000
4.750 0.6530 0.01701 0.00659 -0.0102 0.2407 1.0000
5.000 0.6769 0.01746 0.00705 -0.0095 0.2300 1.0000
5.250 0.7006 0.01794 0.00752 -0.0089 0.2202 1.0000
5.500 0.7239 0.01845 0.00800 -0.0082 0.2113 1.0000
5.750 0.7480 0.01893 0.00859 -0.0076 0.2026 1.0000
6.000 0.7714 0.01947 0.00913 -0.0069 0.1947 1.0000
6.250 0.7948 0.01993 0.00965 -0.0063 0.1846 1.0000
6.500 0.8182 0.02039 0.01020 -0.0057 0.1743 1.0000
6.750 0.8412 0.02091 0.01079 -0.0050 0.1657 1.0000
7.000 0.8644 0.02144 0.01142 -0.0044 0.1577 1.0000
7.250 0.8874 0.02206 0.01215 -0.0037 0.1507 1.0000
7.500 0.9100 0.02265 0.01284 -0.0030 0.1429 1.0000
7.750 0.9324 0.02323 0.01361 -0.0023 0.1334 1.0000
8.000 0.9541 0.02376 0.01425 -0.0016 0.1229 1.0000
8.250 0.9751 0.02436 0.01490 -0.0008 0.1130 1.0000
8.500 0.9963 0.02503 0.01575 0.0000 0.1028 1.0000
8.750 1.0169 0.02580 0.01667 0.0008 0.0925 1.0000
9.000 1.0364 0.02667 0.01768 0.0017 0.0833 1.0000
9.250 1.0547 0.02762 0.01870 0.0027 0.0757 1.0000
9.500 1.0732 0.02872 0.01999 0.0038 0.0679 1.0000
9.750 1.0891 0.02991 0.02125 0.0049 0.0618 1.0000
10.000 1.1048 0.03127 0.02281 0.0062 0.0567 1.0000
10.250 1.1175 0.03278 0.02439 0.0076 0.0531 1.0000
10.500 1.1297 0.03457 0.02640 0.0091 0.0500 1.0000
10.750 1.1409 0.03631 0.02843 0.0106 0.0466 1.0000
11.000 1.1499 0.03796 0.03024 0.0121 0.0438 1.0000
11.250 1.1553 0.03992 0.03229 0.0138 0.0418 1.0000
11.500 1.1583 0.04228 0.03485 0.0157 0.0404 1.0000
11.750 1.1575 0.04469 0.03758 0.0179 0.0394 1.0000
12.000 1.1534 0.04743 0.04062 0.0197 0.0384 1.0000
12.250 1.1464 0.05054 0.04401 0.0209 0.0375 1.0000
12.500 1.1366 0.05410 0.04784 0.0213 0.0367 1.0000
12.750 1.1240 0.05828 0.05226 0.0207 0.0361 1.0000
13.000 1.1080 0.06335 0.05757 0.0189 0.0358 1.0000
13.250 1.0871 0.06988 0.06433 0.0154 0.0357 1.0000
13.500 1.0577 0.07905 0.07373 0.0093 0.0361 1.0000
13.750 1.0154 0.09254 0.08742 -0.0002 0.0373 1.0000
14.000 0.9539 0.11167 0.10658 -0.0120 0.0388 1.0000
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Polar data table (+)
Polar graphs
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