BOEING-VERTOL VR-1 AIRFOIL (vr1-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: BOEING-VERTOL VR-1 AIRFOIL (vr1-il) Reynolds number: 50,000 Max Cl/Cd: 30.02 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-vr1-il-50000-n5.txt Download as CSV file: xf-vr1-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: BOEING-VERTOL VR-1 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.5356 0.08837 0.08047 -0.0460 1.0000 0.0579
-10.000 -0.5393 0.08383 0.07597 -0.0480 1.0000 0.0574
-9.750 -0.5504 0.07886 0.07104 -0.0505 1.0000 0.0568
-9.500 -0.5658 0.07441 0.06659 -0.0519 1.0000 0.0563
-9.250 -0.5845 0.07067 0.06285 -0.0514 1.0000 0.0558
-9.000 -0.6014 0.06702 0.05913 -0.0502 1.0000 0.0554
-8.750 -0.6153 0.06347 0.05546 -0.0486 1.0000 0.0550
-8.500 -0.6261 0.06011 0.05195 -0.0465 1.0000 0.0546
-8.250 -0.6341 0.05687 0.04850 -0.0441 1.0000 0.0543
-8.000 -0.6392 0.05376 0.04515 -0.0416 1.0000 0.0541
-7.750 -0.6407 0.05090 0.04201 -0.0389 1.0000 0.0539
-7.500 -0.6399 0.04821 0.03903 -0.0362 1.0000 0.0538
-7.250 -0.6366 0.04575 0.03626 -0.0334 1.0000 0.0541
-7.000 -0.6309 0.04348 0.03368 -0.0308 1.0000 0.0547
-6.750 -0.6232 0.04135 0.03121 -0.0283 1.0000 0.0556
-6.500 -0.6132 0.03934 0.02884 -0.0258 1.0000 0.0564
-6.250 -0.6010 0.03749 0.02664 -0.0236 1.0000 0.0571
-6.000 -0.5866 0.03576 0.02457 -0.0216 1.0000 0.0577
-5.750 -0.5706 0.03420 0.02275 -0.0197 1.0000 0.0581
-5.500 -0.5537 0.03269 0.02115 -0.0181 1.0000 0.0590
-5.250 -0.5364 0.03143 0.01981 -0.0165 1.0000 0.0600
-5.000 -0.5187 0.03035 0.01863 -0.0149 1.0000 0.0613
-4.750 -0.5011 0.02940 0.01760 -0.0132 1.0000 0.0637
-4.500 -0.4831 0.02857 0.01663 -0.0116 1.0000 0.0664
-4.250 -0.4651 0.02780 0.01574 -0.0099 1.0000 0.0691
-4.000 -0.4452 0.02699 0.01492 -0.0089 0.9989 0.0722
-3.750 -0.4129 0.02623 0.01406 -0.0101 0.9932 0.0769
-3.500 -0.3814 0.02547 0.01325 -0.0113 0.9872 0.0845
-3.250 -0.3492 0.02471 0.01252 -0.0127 0.9816 0.1015
-3.000 -0.3205 0.02344 0.01172 -0.0137 0.9754 0.1687
-2.750 -0.2967 0.02181 0.01142 -0.0141 0.9702 0.4023
-2.500 -0.2829 0.02093 0.01210 -0.0096 0.9638 0.6949
-2.250 -0.2389 0.02158 0.01311 -0.0087 0.9618 0.8704
-2.000 -0.1684 0.02223 0.01344 -0.0154 0.9620 0.9325
-1.750 -0.1014 0.02248 0.01334 -0.0230 0.9608 0.9609
-1.500 -0.0420 0.02254 0.01312 -0.0299 0.9580 0.9804
-1.250 0.0195 0.02256 0.01291 -0.0374 0.9561 1.0000
-1.000 0.0428 0.02254 0.01276 -0.0379 0.9462 1.0000
-0.750 0.0743 0.02260 0.01268 -0.0397 0.9387 1.0000
-0.500 0.0968 0.02267 0.01265 -0.0397 0.9290 1.0000
-0.250 0.1255 0.02279 0.01267 -0.0407 0.9212 1.0000
0.000 0.1497 0.02293 0.01273 -0.0409 0.9122 1.0000
0.250 0.1780 0.02310 0.01283 -0.0416 0.9045 1.0000
0.500 0.2018 0.02329 0.01298 -0.0415 0.8956 1.0000
0.750 0.2323 0.02349 0.01314 -0.0425 0.8884 1.0000
1.000 0.2539 0.02373 0.01337 -0.0419 0.8790 1.0000
1.250 0.2849 0.02394 0.01358 -0.0429 0.8720 1.0000
1.500 0.3052 0.02422 0.01386 -0.0419 0.8621 1.0000
1.750 0.3335 0.02446 0.01413 -0.0423 0.8543 1.0000
2.000 0.3561 0.02474 0.01445 -0.0416 0.8446 1.0000
2.250 0.3802 0.02502 0.01478 -0.0412 0.8354 1.0000
2.500 0.4084 0.02523 0.01507 -0.0413 0.8265 1.0000
2.750 0.4281 0.02555 0.01548 -0.0400 0.8155 1.0000
3.000 0.4659 0.02556 0.01563 -0.0413 0.8075 1.0000
3.250 0.4950 0.02540 0.01559 -0.0407 0.7917 1.0000
3.500 0.5278 0.02449 0.01480 -0.0391 0.7635 1.0000
3.750 0.5687 0.02275 0.01313 -0.0374 0.7234 1.0000
4.000 0.5879 0.02217 0.01261 -0.0340 0.6876 1.0000
4.250 0.6058 0.02185 0.01237 -0.0308 0.6507 1.0000
4.500 0.6227 0.02156 0.01209 -0.0273 0.5994 1.0000
4.750 0.6403 0.02133 0.01155 -0.0236 0.4906 1.0000
5.000 0.6437 0.02259 0.01143 -0.0184 0.2948 1.0000
5.500 0.6512 0.02580 0.01350 -0.0116 0.1740 1.0000
5.750 0.6623 0.02703 0.01454 -0.0092 0.1524 1.0000
6.000 0.6757 0.02819 0.01559 -0.0072 0.1371 1.0000
6.250 0.6918 0.02932 0.01668 -0.0054 0.1250 1.0000
6.500 0.7111 0.03049 0.01778 -0.0042 0.1155 1.0000
6.750 0.7348 0.03161 0.01893 -0.0035 0.1064 1.0000
7.000 0.7649 0.03290 0.02026 -0.0036 0.0993 1.0000
7.250 0.7939 0.03419 0.02163 -0.0036 0.0930 1.0000
7.500 0.8236 0.03575 0.02317 -0.0039 0.0878 1.0000
7.750 0.8525 0.03746 0.02515 -0.0039 0.0839 1.0000
8.000 0.8776 0.03921 0.02706 -0.0036 0.0805 1.0000
8.250 0.9005 0.04098 0.02886 -0.0032 0.0775 1.0000
8.500 0.9198 0.04307 0.03120 -0.0023 0.0750 1.0000
8.750 0.9359 0.04535 0.03390 -0.0009 0.0730 1.0000
9.000 0.9497 0.04787 0.03678 0.0007 0.0716 1.0000
9.250 0.9603 0.05047 0.03972 0.0024 0.0705 1.0000
9.500 0.9680 0.05306 0.04261 0.0043 0.0693 1.0000
9.750 0.9742 0.05555 0.04534 0.0061 0.0680 1.0000
10.000 0.9812 0.05796 0.04791 0.0077 0.0667 1.0000
10.250 0.9875 0.06051 0.05057 0.0092 0.0654 1.0000
10.500 0.9846 0.06359 0.05385 0.0113 0.0648 1.0000
10.750 0.9712 0.06675 0.05733 0.0143 0.0645 1.0000
11.000 0.9542 0.07003 0.06085 0.0171 0.0644 1.0000
11.250 0.9363 0.07363 0.06465 0.0189 0.0644 1.0000
11.500 0.9158 0.07772 0.06894 0.0198 0.0645 1.0000
11.750 0.8943 0.08237 0.07375 0.0195 0.0646 1.0000
12.000 0.8717 0.08772 0.07924 0.0181 0.0648 1.0000
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Polar data table (+)
Polar graphs
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