BOEING-VERTOL VR-13 AIRFOIL (vr13-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: BOEING-VERTOL VR-13 AIRFOIL (vr13-il) Reynolds number: 200,000 Max Cl/Cd: 49.59 at α=2.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-vr13-il-200000.txt Download as CSV file: xf-vr13-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3905 0.08868 0.08552 -0.0139 1.0000 0.0385
-8.750 -0.3924 0.08439 0.08126 -0.0156 1.0000 0.0398
-8.500 -0.5138 0.08705 0.08381 -0.0155 1.0000 0.0352
-8.250 -0.5112 0.08324 0.08002 -0.0175 1.0000 0.0357
-8.000 -0.5102 0.07942 0.07621 -0.0195 1.0000 0.0364
-7.750 -0.5076 0.07528 0.07204 -0.0220 1.0000 0.0372
-7.500 -0.5038 0.07101 0.06773 -0.0245 1.0000 0.0382
-7.250 -0.4988 0.06672 0.06336 -0.0267 1.0000 0.0400
-7.000 -0.4940 0.06237 0.05864 -0.0294 1.0000 0.0434
-6.750 -0.4958 0.06065 0.05656 -0.0271 1.0000 0.0439
-6.250 -0.5027 0.05221 0.04833 -0.0221 1.0000 0.0463
-6.000 -0.5023 0.05051 0.04663 -0.0190 1.0000 0.0478
-5.750 -0.5018 0.04850 0.04453 -0.0159 1.0000 0.0496
-5.500 -0.4968 0.04611 0.04194 -0.0134 0.9996 0.0526
-5.250 -0.4700 0.04115 0.03643 -0.0154 0.9949 0.0582
-5.000 -0.4419 0.03842 0.03368 -0.0171 0.9908 0.0621
-4.750 -0.4124 0.03516 0.02994 -0.0184 0.9863 0.0724
-4.500 -0.3835 0.03303 0.02763 -0.0198 0.9818 0.0867
-4.250 -0.3536 0.03087 0.02532 -0.0213 0.9774 0.1021
-4.000 -0.3110 0.02421 0.01729 -0.0192 0.9750 0.0542
-3.750 -0.2787 0.02175 0.01448 -0.0196 0.9707 0.0530
-3.500 -0.2424 0.02082 0.01324 -0.0209 0.9668 0.0555
-3.250 -0.2035 0.01932 0.01151 -0.0227 0.9644 0.0563
-3.000 -0.1642 0.01746 0.00964 -0.0252 0.9628 0.0602
-2.750 -0.1345 0.01669 0.00885 -0.0254 0.9567 0.0624
-2.500 -0.0973 0.01590 0.00805 -0.0271 0.9525 0.0654
-2.250 -0.0616 0.01537 0.00748 -0.0283 0.9450 0.0696
-2.000 -0.0276 0.01442 0.00661 -0.0290 0.9365 0.0749
-1.750 -0.0018 0.01399 0.00616 -0.0280 0.9247 0.0815
-1.500 0.0223 0.01352 0.00571 -0.0266 0.9141 0.0947
-1.250 0.0704 0.01033 0.00568 -0.0293 0.9100 0.9275
-1.000 0.1770 0.01058 0.00569 -0.0435 0.9077 1.0000
-0.750 0.1968 0.01048 0.00549 -0.0416 0.8949 1.0000
-0.500 0.2174 0.01039 0.00530 -0.0399 0.8830 1.0000
-0.250 0.2381 0.01030 0.00511 -0.0381 0.8714 1.0000
0.000 0.2589 0.01019 0.00491 -0.0362 0.8598 1.0000
0.250 0.2808 0.01009 0.00473 -0.0346 0.8470 1.0000
0.500 0.3034 0.00999 0.00456 -0.0332 0.8331 1.0000
0.750 0.3262 0.00990 0.00439 -0.0317 0.8183 1.0000
1.000 0.3491 0.00980 0.00422 -0.0303 0.8024 1.0000
1.250 0.3725 0.00973 0.00406 -0.0290 0.7846 1.0000
1.500 0.3964 0.00968 0.00394 -0.0278 0.7631 1.0000
1.750 0.4201 0.00965 0.00381 -0.0265 0.7390 1.0000
2.000 0.4442 0.00964 0.00371 -0.0254 0.7072 1.0000
2.250 0.4681 0.00967 0.00358 -0.0242 0.6606 1.0000
2.500 0.4909 0.00990 0.00342 -0.0228 0.5732 1.0000
2.750 0.5125 0.01067 0.00347 -0.0217 0.4485 1.0000
3.000 0.5352 0.01139 0.00373 -0.0211 0.3729 1.0000
3.250 0.5585 0.01196 0.00401 -0.0205 0.3359 1.0000
3.500 0.5823 0.01241 0.00429 -0.0199 0.3117 1.0000
3.750 0.6060 0.01285 0.00458 -0.0193 0.2940 1.0000
4.000 0.6297 0.01327 0.00490 -0.0187 0.2793 1.0000
4.250 0.6536 0.01366 0.00523 -0.0180 0.2667 1.0000
4.500 0.6772 0.01408 0.00557 -0.0173 0.2554 1.0000
4.750 0.7006 0.01456 0.00594 -0.0167 0.2456 1.0000
5.000 0.7247 0.01488 0.00629 -0.0160 0.2362 1.0000
5.250 0.7482 0.01538 0.00671 -0.0153 0.2287 1.0000
5.500 0.7720 0.01575 0.00711 -0.0146 0.2212 1.0000
5.750 0.7955 0.01631 0.00760 -0.0139 0.2149 1.0000
6.000 0.8194 0.01665 0.00802 -0.0133 0.2081 1.0000
6.250 0.8427 0.01721 0.00846 -0.0126 0.2017 1.0000
6.500 0.8662 0.01751 0.00891 -0.0119 0.1951 1.0000
6.750 0.8896 0.01795 0.00933 -0.0112 0.1897 1.0000
7.000 0.9130 0.01854 0.00993 -0.0105 0.1848 1.0000
7.250 0.9362 0.01894 0.01043 -0.0098 0.1794 1.0000
7.500 0.9593 0.01939 0.01089 -0.0091 0.1745 1.0000
7.750 0.9822 0.01999 0.01155 -0.0084 0.1697 1.0000
8.000 1.0048 0.02041 0.01209 -0.0076 0.1645 1.0000
8.250 1.0275 0.02092 0.01259 -0.0069 0.1600 1.0000
8.500 1.0497 0.02159 0.01338 -0.0061 0.1553 1.0000
8.750 1.0711 0.02195 0.01386 -0.0052 0.1494 1.0000
9.000 1.0927 0.02258 0.01440 -0.0045 0.1435 1.0000
9.250 1.1123 0.02281 0.01488 -0.0032 0.1370 1.0000
9.500 1.1328 0.02327 0.01530 -0.0023 0.1310 1.0000
9.750 1.1516 0.02376 0.01602 -0.0011 0.1243 1.0000
10.000 1.1707 0.02420 0.01643 0.0000 0.1180 1.0000
10.250 1.1885 0.02485 0.01727 0.0013 0.1112 1.0000
10.500 1.2060 0.02533 0.01774 0.0026 0.1050 1.0000
10.750 1.2224 0.02608 0.01869 0.0040 0.0985 1.0000
11.000 1.2383 0.02666 0.01929 0.0055 0.0928 1.0000
11.250 1.2527 0.02760 0.02037 0.0071 0.0869 1.0000
11.500 1.2663 0.02820 0.02106 0.0088 0.0814 1.0000
11.750 1.2776 0.02931 0.02224 0.0106 0.0763 1.0000
12.000 1.2878 0.03017 0.02324 0.0126 0.0715 1.0000
12.250 1.2939 0.03148 0.02451 0.0150 0.0676 1.0000
12.500 1.2995 0.03285 0.02611 0.0173 0.0644 1.0000
12.750 1.3049 0.03417 0.02756 0.0193 0.0611 1.0000
13.000 1.3090 0.03568 0.02910 0.0212 0.0584 1.0000
13.250 1.3116 0.03793 0.03142 0.0229 0.0559 1.0000
13.500 1.3120 0.03997 0.03371 0.0245 0.0541 1.0000
13.750 1.3119 0.04221 0.03615 0.0258 0.0523 1.0000
14.000 1.3115 0.04456 0.03864 0.0268 0.0507 1.0000
14.250 1.3107 0.04701 0.04119 0.0275 0.0493 1.0000
14.500 1.3085 0.04983 0.04409 0.0281 0.0478 1.0000
15.000 1.2873 0.05798 0.05265 0.0282 0.0459 1.0000
15.250 1.2738 0.06245 0.05736 0.0269 0.0455 1.0000
15.500 1.2574 0.06766 0.06281 0.0249 0.0450 1.0000
15.750 1.2379 0.07382 0.06919 0.0220 0.0447 1.0000
16.000 1.2143 0.08112 0.07672 0.0180 0.0446 1.0000
16.250 1.1853 0.09007 0.08588 0.0126 0.0447 1.0000
16.500 1.1480 0.10129 0.09731 0.0057 0.0451 1.0000
16.750 1.0937 0.11683 0.11303 -0.0037 0.0460 1.0000
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Polar data table (+)
Polar graphs
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