BOEING-VERTOL VR-5 AIRFOIL (vr5-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: BOEING-VERTOL VR-5 AIRFOIL (vr5-il) Reynolds number: 500,000 Max Cl/Cd: 105.11 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-vr5-il-500000-n5.txt Download as CSV file: xf-vr5-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: BOEING-VERTOL VR-5 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5034 0.08626 0.08365 -0.0091 0.7846 0.0093
-9.000 -0.5141 0.07846 0.07584 -0.0153 0.7762 0.0095
-8.750 -0.5278 0.06894 0.06627 -0.0274 0.7664 0.0096
-8.500 -0.5453 0.05694 0.05402 -0.0368 0.7587 0.0098
-8.000 -0.5309 0.04606 0.04265 -0.0415 0.7425 0.0101
-7.750 -0.5564 0.02179 0.01644 -0.0428 0.7392 0.0114
-7.500 -0.5338 0.01935 0.01354 -0.0426 0.7317 0.0118
-7.250 -0.5089 0.01785 0.01169 -0.0424 0.7238 0.0123
-7.000 -0.4827 0.01700 0.01067 -0.0424 0.7167 0.0128
-6.750 -0.4555 0.01660 0.01019 -0.0425 0.7097 0.0132
-6.500 -0.4283 0.01611 0.00959 -0.0425 0.7035 0.0136
-6.250 -0.4012 0.01548 0.00884 -0.0426 0.6974 0.0141
-6.000 -0.3741 0.01482 0.00802 -0.0425 0.6914 0.0148
-5.750 -0.3470 0.01416 0.00720 -0.0425 0.6859 0.0155
-5.500 -0.3195 0.01365 0.00662 -0.0426 0.6800 0.0162
-5.250 -0.2916 0.01340 0.00631 -0.0427 0.6742 0.0169
-5.000 -0.2636 0.01310 0.00595 -0.0428 0.6685 0.0180
-4.750 -0.2356 0.01278 0.00554 -0.0428 0.6624 0.0195
-4.250 -0.1793 0.01229 0.00498 -0.0432 0.6517 0.0221
-4.000 -0.1511 0.01203 0.00466 -0.0433 0.6461 0.0237
-3.750 -0.1227 0.01184 0.00436 -0.0434 0.6411 0.0247
-3.500 -0.0948 0.01143 0.00396 -0.0436 0.6358 0.0263
-3.250 -0.0664 0.01124 0.00374 -0.0438 0.6301 0.0277
-3.000 -0.0378 0.01110 0.00356 -0.0440 0.6250 0.0297
-2.750 -0.0091 0.01099 0.00341 -0.0442 0.6195 0.0312
-2.500 0.0191 0.01063 0.00302 -0.0444 0.6146 0.0331
-2.250 0.0476 0.01043 0.00277 -0.0446 0.6101 0.0344
-2.000 0.0763 0.01025 0.00257 -0.0448 0.6051 0.0358
-1.750 0.1051 0.01010 0.00239 -0.0451 0.6001 0.0374
-1.250 0.1627 0.00986 0.00207 -0.0456 0.5912 0.0423
-1.000 0.1916 0.00974 0.00195 -0.0458 0.5860 0.0469
-0.500 0.2490 0.00941 0.00178 -0.0464 0.5768 0.1108
-0.250 0.2763 0.00854 0.00165 -0.0471 0.5728 0.3745
0.000 0.3025 0.00776 0.00165 -0.0473 0.5694 0.6211
0.250 0.3304 0.00766 0.00167 -0.0473 0.5657 0.6762
0.500 0.3585 0.00757 0.00172 -0.0474 0.5611 0.7151
0.750 0.3861 0.00753 0.00177 -0.0473 0.5557 0.7587
1.000 0.4129 0.00750 0.00183 -0.0469 0.5511 0.8003
1.250 0.4409 0.00749 0.00188 -0.0469 0.5472 0.8207
1.500 0.4690 0.00750 0.00192 -0.0470 0.5434 0.8332
1.750 0.4970 0.00753 0.00197 -0.0470 0.5398 0.8451
2.000 0.5248 0.00758 0.00203 -0.0470 0.5361 0.8579
2.250 0.5524 0.00761 0.00209 -0.0469 0.5322 0.8727
2.500 0.5797 0.00763 0.00217 -0.0467 0.5279 0.8889
2.750 0.6067 0.00768 0.00224 -0.0466 0.5236 0.9058
3.250 0.6612 0.00776 0.00238 -0.0463 0.5158 0.9389
3.500 0.6904 0.00779 0.00244 -0.0466 0.5102 0.9556
3.750 0.7233 0.00787 0.00250 -0.0478 0.5038 0.9732
4.000 0.7568 0.00791 0.00260 -0.0492 0.4978 1.0000
4.250 0.7854 0.00802 0.00270 -0.0495 0.4911 1.0000
4.500 0.8141 0.00811 0.00281 -0.0499 0.4822 1.0000
4.750 0.8425 0.00824 0.00293 -0.0502 0.4717 1.0000
5.000 0.8707 0.00838 0.00305 -0.0505 0.4570 1.0000
5.250 0.8987 0.00855 0.00319 -0.0508 0.4396 1.0000
5.500 0.9257 0.00885 0.00339 -0.0510 0.4097 1.0000
5.750 0.9505 0.00946 0.00374 -0.0511 0.3597 1.0000
6.000 0.9735 0.01034 0.00427 -0.0511 0.2930 1.0000
6.250 0.9970 0.01109 0.00480 -0.0511 0.2528 1.0000
6.500 1.0219 0.01161 0.00522 -0.0511 0.2277 1.0000
6.750 1.0464 0.01216 0.00566 -0.0511 0.2001 1.0000
7.000 1.0661 0.01325 0.00639 -0.0508 0.1363 1.0000
7.250 1.0881 0.01402 0.00703 -0.0506 0.1097 1.0000
7.500 1.1093 0.01480 0.00768 -0.0502 0.0818 1.0000
7.750 1.1311 0.01548 0.00828 -0.0499 0.0659 1.0000
8.000 1.1533 0.01607 0.00885 -0.0497 0.0561 1.0000
8.250 1.1747 0.01670 0.00945 -0.0493 0.0471 1.0000
8.500 1.1953 0.01736 0.01010 -0.0489 0.0389 1.0000
8.750 1.2149 0.01807 0.01078 -0.0483 0.0326 1.0000
9.000 1.2343 0.01875 0.01149 -0.0478 0.0284 1.0000
9.250 1.2519 0.01951 0.01227 -0.0471 0.0249 1.0000
9.500 1.2670 0.02033 0.01312 -0.0461 0.0221 1.0000
9.750 1.2808 0.02130 0.01413 -0.0452 0.0200 1.0000
10.000 1.2952 0.02226 0.01514 -0.0444 0.0185 1.0000
10.250 1.3083 0.02335 0.01629 -0.0435 0.0173 1.0000
10.500 1.3198 0.02460 0.01758 -0.0427 0.0163 1.0000
10.750 1.3312 0.02589 0.01893 -0.0419 0.0156 1.0000
11.000 1.3427 0.02719 0.02031 -0.0412 0.0150 1.0000
11.250 1.3532 0.02860 0.02180 -0.0406 0.0145 1.0000
11.500 1.3629 0.03012 0.02339 -0.0399 0.0140 1.0000
11.750 1.3715 0.03178 0.02513 -0.0393 0.0136 1.0000
12.000 1.3790 0.03356 0.02698 -0.0387 0.0133 1.0000
12.250 1.3849 0.03553 0.02901 -0.0382 0.0130 1.0000
12.500 1.3889 0.03770 0.03127 -0.0376 0.0126 1.0000
12.750 1.3915 0.04004 0.03369 -0.0371 0.0124 1.0000
13.000 1.3967 0.04215 0.03589 -0.0367 0.0122 1.0000
13.250 1.4010 0.04437 0.03820 -0.0363 0.0119 1.0000
13.500 1.4043 0.04671 0.04065 -0.0360 0.0117 1.0000
13.750 1.4067 0.04919 0.04323 -0.0357 0.0115 1.0000
14.000 1.4086 0.05179 0.04592 -0.0355 0.0113 1.0000
14.250 1.4101 0.05452 0.04875 -0.0355 0.0111 1.0000
14.500 1.4111 0.05736 0.05168 -0.0355 0.0109 1.0000
14.750 1.4119 0.06028 0.05469 -0.0356 0.0107 1.0000
15.000 1.4121 0.06330 0.05781 -0.0358 0.0105 1.0000
15.250 1.4119 0.06645 0.06105 -0.0361 0.0103 1.0000
15.500 1.4106 0.06982 0.06450 -0.0366 0.0102 1.0000
15.750 1.4077 0.07341 0.06819 -0.0371 0.0100 1.0000
16.000 1.4033 0.07726 0.07212 -0.0377 0.0098 1.0000
16.250 1.3972 0.08141 0.07636 -0.0384 0.0096 1.0000
16.500 1.3930 0.08538 0.08045 -0.0392 0.0095 1.0000
16.750 1.3907 0.08918 0.08437 -0.0402 0.0094 1.0000
17.000 1.3871 0.09322 0.08853 -0.0412 0.0093 1.0000
17.250 1.3830 0.09742 0.09285 -0.0424 0.0092 1.0000
17.500 1.3783 0.10177 0.09733 -0.0437 0.0090 1.0000
17.750 1.3731 0.10628 0.10196 -0.0452 0.0089 1.0000
18.000 1.3673 0.11091 0.10672 -0.0468 0.0088 1.0000
18.250 1.3612 0.11571 0.11163 -0.0486 0.0087 1.0000
18.500 1.3548 0.12064 0.11668 -0.0506 0.0086 1.0000
18.750 1.3482 0.12569 0.12186 -0.0528 0.0085 1.0000
19.000 1.3412 0.13090 0.12719 -0.0552 0.0084 1.0000
19.250 1.3340 0.13622 0.13262 -0.0577 0.0082 1.0000
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Polar data table (+)
Polar graphs
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