BOEING-VERTOL VR-13 AIRFOIL (vr13-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: BOEING-VERTOL VR-13 AIRFOIL (vr13-il) Reynolds number: 500,000 Max Cl/Cd: 74.54 at α=9.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-vr13-il-500000.txt Download as CSV file: xf-vr13-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4041 0.09714 0.09510 -0.0075 1.0000 0.0167
-9.500 -0.4039 0.09308 0.09106 -0.0087 1.0000 0.0169
-9.250 -0.5345 0.09542 0.09331 -0.0028 1.0000 0.0160
-9.000 -0.5320 0.09162 0.08953 -0.0046 1.0000 0.0162
-8.750 -0.5297 0.08767 0.08560 -0.0070 1.0000 0.0163
-8.500 -0.5290 0.08314 0.08110 -0.0107 1.0000 0.0164
-8.250 -0.5322 0.07766 0.07562 -0.0168 1.0000 0.0165
-8.000 -0.5315 0.07285 0.07079 -0.0205 1.0000 0.0166
-7.750 -0.5273 0.06797 0.06585 -0.0239 1.0000 0.0168
-7.500 -0.5213 0.06324 0.06104 -0.0266 1.0000 0.0170
-7.250 -0.5143 0.05870 0.05641 -0.0283 1.0000 0.0172
-7.000 -0.5327 0.04319 0.04030 -0.0289 0.9960 0.0126
-6.750 -0.5414 0.02409 0.01961 -0.0264 0.9855 0.0119
-6.500 -0.5188 0.02066 0.01565 -0.0261 0.9791 0.0128
-6.250 -0.4881 0.02058 0.01556 -0.0269 0.9744 0.0135
-6.000 -0.4652 0.01877 0.01336 -0.0257 0.9667 0.0152
-5.750 -0.4425 0.01815 0.01263 -0.0247 0.9591 0.0166
-5.500 -0.4192 0.01865 0.01319 -0.0238 0.9511 0.0178
-5.250 -0.3958 0.01835 0.01268 -0.0225 0.9433 0.0201
-5.000 -0.3761 0.01701 0.01119 -0.0208 0.9363 0.0218
-4.750 -0.3520 0.01677 0.01093 -0.0200 0.9286 0.0233
-4.500 -0.3287 0.01661 0.01064 -0.0187 0.9221 0.0256
-4.250 -0.3048 0.01540 0.00931 -0.0178 0.9152 0.0280
-4.000 -0.2805 0.01492 0.00879 -0.0169 0.9090 0.0296
-3.750 -0.2552 0.01423 0.00802 -0.0161 0.9033 0.0311
-3.500 -0.2295 0.01363 0.00734 -0.0154 0.8966 0.0325
-3.250 -0.2046 0.01342 0.00702 -0.0143 0.8891 0.0337
-3.000 -0.1819 0.01209 0.00564 -0.0130 0.8798 0.0359
-2.750 -0.1575 0.01156 0.00509 -0.0121 0.8707 0.0376
-2.500 -0.1327 0.01119 0.00468 -0.0111 0.8621 0.0399
-2.250 -0.1068 0.01081 0.00426 -0.0104 0.8524 0.0417
-2.000 -0.0813 0.01049 0.00387 -0.0097 0.8434 0.0432
-1.750 -0.0555 0.01013 0.00345 -0.0090 0.8336 0.0446
-1.500 -0.0299 0.00970 0.00299 -0.0083 0.8238 0.0484
-1.250 -0.0035 0.00947 0.00271 -0.0077 0.8147 0.0518
-1.000 0.0237 0.00928 0.00248 -0.0074 0.8050 0.0557
-0.750 0.0498 0.00891 0.00224 -0.0068 0.7958 0.0917
-0.500 0.0597 0.00676 0.00197 -0.0039 0.7873 0.6375
-0.250 0.1070 0.00605 0.00224 -0.0071 0.7770 0.9455
0.000 0.1650 0.00647 0.00257 -0.0129 0.7646 0.9797
0.250 0.2383 0.00678 0.00275 -0.0224 0.7483 0.9988
0.500 0.2696 0.00678 0.00266 -0.0231 0.7313 1.0000
0.750 0.2964 0.00677 0.00255 -0.0228 0.7116 1.0000
1.000 0.3233 0.00679 0.00245 -0.0226 0.6842 1.0000
1.250 0.3504 0.00686 0.00236 -0.0224 0.6467 1.0000
1.500 0.3777 0.00708 0.00229 -0.0224 0.5804 1.0000
1.750 0.4055 0.00755 0.00231 -0.0227 0.4849 1.0000
2.000 0.4329 0.00805 0.00241 -0.0230 0.3998 1.0000
2.250 0.4597 0.00847 0.00252 -0.0231 0.3389 1.0000
2.500 0.4861 0.00877 0.00262 -0.0231 0.3050 1.0000
2.750 0.5122 0.00899 0.00272 -0.0229 0.2822 1.0000
3.000 0.5380 0.00921 0.00284 -0.0226 0.2651 1.0000
3.250 0.5636 0.00940 0.00295 -0.0223 0.2508 1.0000
3.500 0.5891 0.00959 0.00308 -0.0219 0.2386 1.0000
3.750 0.6144 0.00979 0.00323 -0.0215 0.2280 1.0000
4.000 0.6395 0.01000 0.00337 -0.0211 0.2184 1.0000
4.250 0.6647 0.01017 0.00353 -0.0207 0.2100 1.0000
4.750 0.7146 0.01058 0.00387 -0.0197 0.1939 1.0000
5.000 0.7390 0.01085 0.00408 -0.0192 0.1861 1.0000
5.250 0.7639 0.01101 0.00426 -0.0187 0.1800 1.0000
5.500 0.7881 0.01129 0.00449 -0.0181 0.1739 1.0000
5.750 0.8126 0.01151 0.00474 -0.0175 0.1689 1.0000
6.000 0.8370 0.01172 0.00494 -0.0170 0.1635 1.0000
6.250 0.8604 0.01208 0.00524 -0.0163 0.1576 1.0000
6.500 0.8851 0.01224 0.00547 -0.0157 0.1536 1.0000
6.750 0.9091 0.01248 0.00572 -0.0151 0.1492 1.0000
7.000 0.9320 0.01286 0.00606 -0.0144 0.1448 1.0000
7.250 0.9558 0.01312 0.00638 -0.0137 0.1417 1.0000
7.500 0.9798 0.01333 0.00665 -0.0131 0.1381 1.0000
7.750 1.0032 0.01360 0.00691 -0.0124 0.1337 1.0000
8.000 1.0255 0.01400 0.00730 -0.0116 0.1293 1.0000
8.250 1.0496 0.01417 0.00757 -0.0110 0.1257 1.0000
8.500 1.0729 0.01442 0.00783 -0.0103 0.1211 1.0000
8.750 1.0944 0.01487 0.00826 -0.0094 0.1163 1.0000
9.000 1.1185 0.01502 0.00851 -0.0089 0.1123 1.0000
9.250 1.1412 0.01531 0.00882 -0.0081 0.1071 1.0000
9.500 1.1628 0.01570 0.00924 -0.0073 0.1020 1.0000
9.750 1.1858 0.01594 0.00954 -0.0066 0.0961 1.0000
10.000 1.2068 0.01637 0.00996 -0.0057 0.0893 1.0000
10.250 1.2286 0.01671 0.01034 -0.0049 0.0822 1.0000
10.500 1.2489 0.01719 0.01084 -0.0038 0.0754 1.0000
10.750 1.2681 0.01775 0.01137 -0.0027 0.0682 1.0000
11.000 1.2872 0.01830 0.01197 -0.0016 0.0626 1.0000
11.250 1.3030 0.01912 0.01275 0.0000 0.0564 1.0000
11.500 1.3210 0.01973 0.01345 0.0012 0.0524 1.0000
11.750 1.3335 0.02076 0.01448 0.0031 0.0474 1.0000
12.000 1.3498 0.02143 0.01526 0.0045 0.0443 1.0000
12.250 1.3650 0.02216 0.01606 0.0060 0.0410 1.0000
12.500 1.3724 0.02331 0.01723 0.0085 0.0376 1.0000
12.750 1.3833 0.02408 0.01810 0.0106 0.0358 1.0000
13.000 1.3950 0.02486 0.01897 0.0124 0.0339 1.0000
13.250 1.4042 0.02586 0.02004 0.0142 0.0322 1.0000
13.500 1.4097 0.02719 0.02144 0.0162 0.0305 1.0000
13.750 1.4087 0.02908 0.02343 0.0184 0.0290 1.0000
14.000 1.4181 0.03027 0.02475 0.0196 0.0282 1.0000
14.250 1.4251 0.03172 0.02631 0.0207 0.0272 1.0000
14.500 1.4310 0.03333 0.02803 0.0216 0.0261 1.0000
14.750 1.4341 0.03527 0.03005 0.0224 0.0251 1.0000
15.000 1.4330 0.03774 0.03261 0.0230 0.0241 1.0000
15.250 1.4254 0.04103 0.03601 0.0232 0.0233 1.0000
15.500 1.4121 0.04524 0.04037 0.0228 0.0226 1.0000
15.750 1.4101 0.04843 0.04370 0.0221 0.0222 1.0000
16.000 1.4064 0.05205 0.04747 0.0210 0.0218 1.0000
16.250 1.3984 0.05650 0.05208 0.0192 0.0214 1.0000
16.500 1.3860 0.06192 0.05766 0.0167 0.0211 1.0000
16.750 1.3694 0.06840 0.06430 0.0134 0.0209 1.0000
17.000 1.3495 0.07564 0.07170 0.0097 0.0208 1.0000
17.250 1.3267 0.08351 0.07972 0.0058 0.0207 1.0000
17.500 1.3028 0.09146 0.08781 0.0019 0.0207 1.0000
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Polar data table (+)
Polar graphs
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