BOEING-VERTOL VR-13 AIRFOIL (vr13-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: BOEING-VERTOL VR-13 AIRFOIL (vr13-il) Reynolds number: 100,000 Max Cl/Cd: 40.01 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-vr13-il-100000-n5.txt Download as CSV file: xf-vr13-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: BOEING-VERTOL VR-13 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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.5171 0.08246 0.07772 -0.0225 1.0000 0.0260
-8.250 -0.5175 0.07871 0.07398 -0.0235 1.0000 0.0257
-8.000 -0.5173 0.07445 0.06969 -0.0252 1.0000 0.0254
-7.750 -0.5167 0.06994 0.06513 -0.0269 1.0000 0.0251
-7.500 -0.5153 0.06537 0.06046 -0.0281 1.0000 0.0248
-7.250 -0.5132 0.06077 0.05573 -0.0287 1.0000 0.0246
-7.000 -0.5106 0.05617 0.05093 -0.0285 1.0000 0.0248
-6.750 -0.5092 0.05146 0.04591 -0.0272 1.0000 0.0255
-6.500 -0.5115 0.04694 0.04087 -0.0240 1.0000 0.0262
-6.250 -0.5049 0.04547 0.03952 -0.0221 1.0000 0.0273
-6.000 -0.4997 0.04345 0.03734 -0.0194 1.0000 0.0281
-5.750 -0.4952 0.04069 0.03430 -0.0163 1.0000 0.0285
-5.500 -0.4836 0.03772 0.03097 -0.0143 0.9983 0.0290
-5.250 -0.4558 0.03458 0.02729 -0.0150 0.9927 0.0317
-5.000 -0.4269 0.03150 0.02343 -0.0151 0.9870 0.0336
-4.750 -0.3981 0.02865 0.02018 -0.0158 0.9823 0.0349
-4.500 -0.3671 0.02721 0.01864 -0.0171 0.9775 0.0377
-4.250 -0.3331 0.02558 0.01663 -0.0182 0.9738 0.0407
-4.000 -0.3009 0.02409 0.01476 -0.0188 0.9688 0.0428
-3.750 -0.2665 0.02258 0.01311 -0.0202 0.9651 0.0461
-3.500 -0.2328 0.02142 0.01187 -0.0214 0.9610 0.0483
-3.250 -0.2019 0.02051 0.01087 -0.0219 0.9551 0.0510
-3.000 -0.1678 0.01979 0.01004 -0.0231 0.9507 0.0552
-2.750 -0.1402 0.01895 0.00921 -0.0231 0.9441 0.0577
-2.500 -0.1104 0.01831 0.00858 -0.0235 0.9385 0.0616
-2.250 -0.0812 0.01788 0.00810 -0.0237 0.9325 0.0678
-2.000 -0.0537 0.01742 0.00762 -0.0236 0.9257 0.0736
-1.750 -0.0221 0.01701 0.00719 -0.0242 0.9209 0.0847
-1.500 0.0027 0.01644 0.00686 -0.0236 0.9118 0.1287
-1.250 0.1507 0.01379 0.00698 -0.0451 0.9188 1.0000
-1.000 0.1736 0.01366 0.00669 -0.0436 0.8988 1.0000
-0.750 0.1955 0.01354 0.00641 -0.0419 0.8809 1.0000
-0.500 0.2170 0.01343 0.00616 -0.0401 0.8640 1.0000
-0.250 0.2388 0.01334 0.00595 -0.0385 0.8479 1.0000
0.000 0.2612 0.01328 0.00578 -0.0371 0.8327 1.0000
0.250 0.2837 0.01322 0.00562 -0.0356 0.8174 1.0000
0.500 0.3062 0.01316 0.00546 -0.0342 0.8013 1.0000
0.750 0.3290 0.01312 0.00534 -0.0328 0.7832 1.0000
1.000 0.3519 0.01310 0.00522 -0.0314 0.7637 1.0000
1.250 0.3748 0.01307 0.00510 -0.0300 0.7422 1.0000
1.500 0.3979 0.01308 0.00502 -0.0287 0.7154 1.0000
1.750 0.4209 0.01309 0.00493 -0.0273 0.6828 1.0000
2.000 0.4436 0.01314 0.00482 -0.0259 0.6374 1.0000
2.250 0.4655 0.01329 0.00466 -0.0242 0.5699 1.0000
2.500 0.4865 0.01371 0.00459 -0.0225 0.4869 1.0000
2.750 0.5079 0.01428 0.00472 -0.0214 0.4174 1.0000
3.000 0.5298 0.01484 0.00495 -0.0204 0.3681 1.0000
3.250 0.5523 0.01533 0.00521 -0.0196 0.3359 1.0000
3.500 0.5751 0.01577 0.00549 -0.0188 0.3122 1.0000
3.750 0.5980 0.01621 0.00579 -0.0180 0.2942 1.0000
4.000 0.6210 0.01663 0.00613 -0.0172 0.2794 1.0000
4.250 0.6440 0.01704 0.00647 -0.0164 0.2664 1.0000
4.500 0.6670 0.01746 0.00683 -0.0156 0.2551 1.0000
4.750 0.6897 0.01792 0.00722 -0.0148 0.2457 1.0000
5.000 0.7131 0.01832 0.00764 -0.0141 0.2367 1.0000
5.250 0.7358 0.01881 0.00807 -0.0133 0.2295 1.0000
5.500 0.7591 0.01924 0.00854 -0.0125 0.2216 1.0000
5.750 0.7817 0.01976 0.00901 -0.0117 0.2150 1.0000
6.000 0.8048 0.02021 0.00954 -0.0110 0.2076 1.0000
6.250 0.8273 0.02075 0.01003 -0.0102 0.2019 1.0000
6.500 0.8505 0.02128 0.01067 -0.0094 0.1963 1.0000
6.750 0.8733 0.02183 0.01127 -0.0087 0.1911 1.0000
7.000 0.8957 0.02245 0.01184 -0.0079 0.1866 1.0000
7.250 0.9184 0.02298 0.01254 -0.0071 0.1802 1.0000
7.500 0.9402 0.02350 0.01311 -0.0063 0.1743 1.0000
7.750 0.9621 0.02407 0.01379 -0.0055 0.1684 1.0000
8.000 0.9836 0.02461 0.01443 -0.0047 0.1622 1.0000
8.250 1.0049 0.02525 0.01504 -0.0038 0.1578 1.0000
8.500 1.0263 0.02592 0.01598 -0.0030 0.1524 1.0000
8.750 1.0470 0.02653 0.01669 -0.0021 0.1472 1.0000
9.000 1.0672 0.02720 0.01742 -0.0011 0.1423 1.0000
9.250 1.0870 0.02792 0.01838 -0.0001 0.1365 1.0000
9.500 1.1063 0.02860 0.01912 0.0009 0.1318 1.0000
9.750 1.1248 0.02942 0.02016 0.0020 0.1264 1.0000
10.000 1.1421 0.03008 0.02097 0.0032 0.1201 1.0000
10.250 1.1584 0.03079 0.02179 0.0045 0.1142 1.0000
10.500 1.1739 0.03159 0.02280 0.0058 0.1076 1.0000
10.750 1.1881 0.03238 0.02362 0.0073 0.1026 1.0000
11.000 1.2017 0.03345 0.02500 0.0088 0.0963 1.0000
11.250 1.2132 0.03429 0.02590 0.0104 0.0916 1.0000
11.500 1.2235 0.03557 0.02743 0.0121 0.0862 1.0000
11.750 1.2315 0.03672 0.02873 0.0141 0.0816 1.0000
12.000 1.2353 0.03789 0.02991 0.0164 0.0783 1.0000
12.250 1.2388 0.03958 0.03190 0.0184 0.0739 1.0000
12.500 1.2408 0.04116 0.03362 0.0202 0.0704 1.0000
12.750 1.2409 0.04289 0.03542 0.0218 0.0677 1.0000
13.000 1.2392 0.04529 0.03804 0.0230 0.0651 1.0000
13.250 1.2356 0.04796 0.04094 0.0240 0.0626 1.0000
13.500 1.2305 0.05083 0.04398 0.0244 0.0605 1.0000
13.750 1.2241 0.05399 0.04725 0.0244 0.0588 1.0000
14.000 1.2165 0.05746 0.05079 0.0239 0.0573 1.0000
14.250 1.2050 0.06182 0.05530 0.0228 0.0560 1.0000
14.500 1.1876 0.06752 0.06126 0.0205 0.0551 1.0000
14.750 1.1661 0.07437 0.06835 0.0171 0.0545 1.0000
15.000 1.1390 0.08287 0.07707 0.0123 0.0542 1.0000
15.250 1.1027 0.09381 0.08822 0.0058 0.0544 1.0000
15.500 1.0500 0.10896 0.10350 -0.0028 0.0552 1.0000
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Polar data table (+)
Polar graphs
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