BOEING-VERTOL VR-7 AIRFOIL (vr7-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: BOEING-VERTOL VR-7 AIRFOIL (vr7-il) Reynolds number: 1,000,000 Max Cl/Cd: 113.06 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-vr7-il-1000000-n5.txt Download as CSV file: xf-vr7-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: BOEING-VERTOL VR-7 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.8481 0.03688 0.03450 -0.0647 1.0000 0.0076
-12.000 -0.8879 0.03148 0.02867 -0.0598 1.0000 0.0076
-11.750 -0.8879 0.02921 0.02620 -0.0573 1.0000 0.0078
-11.500 -0.8829 0.02738 0.02419 -0.0551 1.0000 0.0079
-11.250 -0.8636 0.02608 0.02278 -0.0549 0.9899 0.0080
-11.000 -0.8303 0.02482 0.02139 -0.0574 0.9752 0.0081
-10.750 -0.7837 0.02421 0.02073 -0.0621 0.9520 0.0083
-10.500 -0.7514 0.02297 0.01922 -0.0643 0.9022 0.0084
-10.250 -0.7362 0.02210 0.01803 -0.0625 0.8492 0.0086
-10.000 -0.7179 0.02163 0.01733 -0.0610 0.8093 0.0087
-9.750 -0.7006 0.02071 0.01616 -0.0596 0.7789 0.0089
-9.500 -0.6810 0.01992 0.01516 -0.0585 0.7573 0.0092
-9.250 -0.6607 0.01906 0.01410 -0.0575 0.7430 0.0094
-9.000 -0.6397 0.01819 0.01302 -0.0565 0.7313 0.0097
-8.500 -0.5953 0.01668 0.01119 -0.0549 0.7105 0.0100
-8.250 -0.5716 0.01615 0.01051 -0.0543 0.7013 0.0101
-8.000 -0.5500 0.01519 0.00940 -0.0534 0.6927 0.0104
-7.750 -0.5262 0.01465 0.00876 -0.0528 0.6858 0.0106
-7.500 -0.5014 0.01421 0.00826 -0.0523 0.6792 0.0107
-7.000 -0.4506 0.01356 0.00749 -0.0514 0.6676 0.0113
-6.750 -0.4251 0.01323 0.00708 -0.0510 0.6615 0.0116
-6.500 -0.3999 0.01284 0.00660 -0.0505 0.6559 0.0118
-6.250 -0.3745 0.01243 0.00612 -0.0500 0.6504 0.0121
-6.000 -0.3490 0.01206 0.00568 -0.0496 0.6448 0.0123
-5.750 -0.3235 0.01171 0.00525 -0.0491 0.6394 0.0126
-5.500 -0.2976 0.01137 0.00485 -0.0487 0.6341 0.0127
-5.250 -0.2715 0.01110 0.00452 -0.0483 0.6292 0.0129
-5.000 -0.2464 0.01069 0.00405 -0.0478 0.6248 0.0133
-4.750 -0.2201 0.01040 0.00376 -0.0475 0.6206 0.0138
-4.500 -0.1936 0.01017 0.00349 -0.0471 0.6154 0.0142
-4.250 -0.1670 0.00997 0.00324 -0.0468 0.6105 0.0146
-4.000 -0.1402 0.00976 0.00300 -0.0466 0.6064 0.0149
-3.750 -0.1133 0.00956 0.00278 -0.0463 0.6013 0.0154
-3.500 -0.0864 0.00939 0.00257 -0.0460 0.5961 0.0158
-3.250 -0.0593 0.00924 0.00238 -0.0458 0.5916 0.0162
-3.000 -0.0322 0.00906 0.00217 -0.0456 0.5868 0.0168
-2.750 -0.0051 0.00890 0.00201 -0.0454 0.5815 0.0177
-2.500 0.0222 0.00879 0.00187 -0.0452 0.5762 0.0189
-2.250 0.0497 0.00869 0.00175 -0.0450 0.5701 0.0202
-2.000 0.0769 0.00858 0.00163 -0.0448 0.5641 0.0227
-1.750 0.1044 0.00849 0.00153 -0.0447 0.5580 0.0260
-1.500 0.1316 0.00839 0.00144 -0.0445 0.5512 0.0339
-1.250 0.1589 0.00830 0.00137 -0.0443 0.5450 0.0465
-1.000 0.1861 0.00819 0.00130 -0.0442 0.5385 0.0688
-0.500 0.2371 0.00754 0.00115 -0.0435 0.5258 0.2494
-0.250 0.2588 0.00683 0.00108 -0.0426 0.5193 0.4635
0.000 0.2838 0.00658 0.00109 -0.0421 0.5134 0.5569
0.250 0.3107 0.00653 0.00110 -0.0419 0.5055 0.5885
0.500 0.3370 0.00646 0.00111 -0.0415 0.4971 0.6262
0.750 0.3624 0.00636 0.00114 -0.0410 0.4881 0.6765
1.000 0.3886 0.00632 0.00116 -0.0406 0.4790 0.7103
1.250 0.4142 0.00629 0.00120 -0.0401 0.4695 0.7474
1.500 0.4400 0.00627 0.00124 -0.0396 0.4589 0.7816
1.750 0.4651 0.00622 0.00129 -0.0389 0.4508 0.8213
2.000 0.4902 0.00619 0.00136 -0.0382 0.4415 0.8640
2.250 0.5172 0.00618 0.00143 -0.0379 0.4341 0.9033
2.500 0.5483 0.00624 0.00152 -0.0385 0.4254 0.9316
2.750 0.5845 0.00634 0.00160 -0.0404 0.4150 0.9512
3.000 0.6226 0.00650 0.00170 -0.0427 0.3995 0.9649
3.250 0.6595 0.00667 0.00181 -0.0448 0.3856 0.9744
3.500 0.6936 0.00681 0.00191 -0.0463 0.3776 0.9805
3.750 0.7248 0.00694 0.00201 -0.0471 0.3693 0.9854
4.000 0.7575 0.00707 0.00212 -0.0483 0.3617 0.9889
4.250 0.7885 0.00723 0.00224 -0.0491 0.3505 0.9925
4.500 0.8195 0.00739 0.00236 -0.0499 0.3382 0.9954
4.750 0.8513 0.00757 0.00249 -0.0510 0.3244 0.9980
5.000 0.8830 0.00781 0.00265 -0.0521 0.3066 0.9999
5.250 0.9059 0.00806 0.00283 -0.0512 0.2890 1.0000
5.500 0.9285 0.00830 0.00301 -0.0503 0.2732 1.0000
5.750 0.9506 0.00857 0.00322 -0.0493 0.2549 1.0000
6.000 0.9717 0.00893 0.00346 -0.0482 0.2324 1.0000
6.250 0.9894 0.00952 0.00384 -0.0465 0.1916 1.0000
6.500 1.0094 0.00995 0.00417 -0.0453 0.1703 1.0000
6.750 1.0287 0.01043 0.00452 -0.0439 0.1440 1.0000
7.000 1.0484 0.01088 0.00485 -0.0426 0.1244 1.0000
7.250 1.0693 0.01123 0.00516 -0.0415 0.1106 1.0000
7.500 1.0878 0.01174 0.00556 -0.0401 0.0906 1.0000
7.750 1.1075 0.01217 0.00593 -0.0388 0.0777 1.0000
8.000 1.1272 0.01258 0.00630 -0.0376 0.0681 1.0000
8.250 1.1477 0.01295 0.00665 -0.0365 0.0623 1.0000
8.500 1.1678 0.01332 0.00701 -0.0353 0.0571 1.0000
8.750 1.1879 0.01368 0.00738 -0.0342 0.0527 1.0000
9.000 1.2068 0.01410 0.00778 -0.0329 0.0481 1.0000
9.250 1.2270 0.01443 0.00814 -0.0318 0.0452 1.0000
9.500 1.2441 0.01491 0.00860 -0.0302 0.0392 1.0000
9.750 1.2606 0.01539 0.00906 -0.0286 0.0341 1.0000
10.000 1.2760 0.01588 0.00955 -0.0268 0.0301 1.0000
10.250 1.2872 0.01642 0.01008 -0.0243 0.0265 1.0000
10.500 1.2995 0.01690 0.01060 -0.0219 0.0246 1.0000
10.750 1.3109 0.01747 0.01119 -0.0196 0.0227 1.0000
11.000 1.3213 0.01814 0.01187 -0.0174 0.0206 1.0000
11.250 1.3334 0.01878 0.01255 -0.0156 0.0197 1.0000
11.500 1.3439 0.01955 0.01336 -0.0137 0.0184 1.0000
11.750 1.3538 0.02043 0.01428 -0.0120 0.0174 1.0000
12.000 1.3634 0.02141 0.01530 -0.0105 0.0166 1.0000
12.250 1.3746 0.02236 0.01631 -0.0093 0.0161 1.0000
12.500 1.3847 0.02347 0.01748 -0.0082 0.0156 1.0000
12.750 1.3940 0.02470 0.01877 -0.0072 0.0150 1.0000
13.000 1.4030 0.02604 0.02016 -0.0064 0.0145 1.0000
13.250 1.4105 0.02758 0.02175 -0.0057 0.0139 1.0000
13.500 1.4172 0.02924 0.02347 -0.0051 0.0135 1.0000
13.750 1.4247 0.03089 0.02518 -0.0046 0.0129 1.0000
14.000 1.4311 0.03267 0.02704 -0.0042 0.0128 1.0000
14.250 1.4383 0.03440 0.02884 -0.0038 0.0123 1.0000
14.500 1.4437 0.03633 0.03084 -0.0036 0.0118 1.0000
14.750 1.4479 0.03841 0.03300 -0.0033 0.0116 1.0000
15.000 1.4509 0.04061 0.03525 -0.0031 0.0111 1.0000
15.250 1.4525 0.04300 0.03771 -0.0030 0.0109 1.0000
15.500 1.4533 0.04551 0.04028 -0.0029 0.0105 1.0000
15.750 1.4517 0.04836 0.04321 -0.0029 0.0103 1.0000
16.000 1.4547 0.05078 0.04571 -0.0031 0.0100 1.0000
16.250 1.4543 0.05365 0.04867 -0.0034 0.0098 1.0000
16.500 1.4548 0.05646 0.05156 -0.0037 0.0095 1.0000
16.750 1.4545 0.05943 0.05461 -0.0042 0.0092 1.0000
17.000 1.4529 0.06264 0.05789 -0.0048 0.0088 1.0000
17.250 1.4503 0.06600 0.06133 -0.0054 0.0086 1.0000
17.500 1.4467 0.06957 0.06498 -0.0062 0.0084 1.0000
17.750 1.4419 0.07335 0.06884 -0.0072 0.0081 1.0000
18.000 1.4360 0.07738 0.07295 -0.0082 0.0079 1.0000
18.250 1.4317 0.08119 0.07686 -0.0093 0.0077 1.0000
18.500 1.4252 0.08542 0.08118 -0.0106 0.0076 1.0000
18.750 1.4194 0.08961 0.08546 -0.0119 0.0073 1.0000
19.000 1.4118 0.09413 0.09007 -0.0135 0.0072 1.0000
19.250 1.4046 0.09863 0.09466 -0.0151 0.0069 1.0000
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Polar data table (+)
Polar graphs
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