WASP (smoothed) (waspsm-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: WASP (smoothed) (waspsm-il) Reynolds number: 200,000 Max Cl/Cd: 69.71 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-waspsm-il-200000.txt Download as CSV file: xf-waspsm-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: WASP (smoothed)
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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4212 0.09706 0.09349 -0.0268 1.0000 0.0498
-8.500 -0.4284 0.09349 0.09000 -0.0307 1.0000 0.0502
-8.250 -0.4343 0.08986 0.08643 -0.0336 1.0000 0.0503
-8.000 -0.4394 0.08376 0.08040 -0.0377 1.0000 0.0507
-7.750 -0.4317 0.08123 0.07789 -0.0315 1.0000 0.0519
-7.500 -0.4251 0.07879 0.07548 -0.0302 1.0000 0.0530
-7.250 -0.4210 0.07588 0.07260 -0.0306 1.0000 0.0542
-7.000 -0.4180 0.07256 0.06931 -0.0321 1.0000 0.0559
-6.750 -0.4160 0.06865 0.06543 -0.0348 1.0000 0.0583
-6.500 -0.4202 0.06160 0.05802 -0.0448 1.0000 0.0624
-6.250 -0.4242 0.05565 0.05204 -0.0446 1.0000 0.0636
-6.000 -0.4158 0.05436 0.05092 -0.0413 1.0000 0.0652
-5.750 -0.4088 0.05262 0.04920 -0.0394 1.0000 0.0671
-5.500 -0.4018 0.04980 0.04629 -0.0388 1.0000 0.0697
-5.250 -0.3961 0.04413 0.03999 -0.0408 1.0000 0.0771
-5.000 -0.3828 0.03294 0.02809 -0.0404 1.0000 0.0476
-4.750 -0.3544 0.02471 0.01850 -0.0413 0.9981 0.0409
-4.500 -0.3155 0.02313 0.01679 -0.0443 0.9940 0.0440
-4.250 -0.2764 0.02124 0.01451 -0.0465 0.9892 0.0469
-4.000 -0.2372 0.01946 0.01231 -0.0485 0.9844 0.0490
-3.750 -0.1983 0.01776 0.01041 -0.0508 0.9797 0.0535
-3.500 -0.1592 0.01677 0.00931 -0.0529 0.9739 0.0582
-3.250 -0.1187 0.01568 0.00810 -0.0552 0.9687 0.0644
-3.000 -0.0789 0.01487 0.00730 -0.0576 0.9630 0.0735
-2.750 -0.0395 0.01400 0.00647 -0.0598 0.9566 0.0863
-2.500 0.0042 0.01315 0.00573 -0.0629 0.9529 0.1098
-2.250 0.0398 0.01245 0.00522 -0.0644 0.9440 0.1534
-2.000 0.0821 0.01154 0.00480 -0.0675 0.9391 0.2623
-1.750 0.1125 0.01081 0.00462 -0.0680 0.9277 0.4081
-1.500 0.1409 0.01012 0.00450 -0.0678 0.9160 0.5669
-1.250 0.2401 0.00879 0.00421 -0.0822 0.9192 1.0000
-1.000 0.2753 0.00871 0.00396 -0.0833 0.9037 1.0000
-0.750 0.3074 0.00865 0.00374 -0.0838 0.8863 1.0000
-0.500 0.3381 0.00861 0.00354 -0.0840 0.8683 1.0000
-0.250 0.3676 0.00860 0.00338 -0.0839 0.8494 1.0000
0.000 0.3944 0.00863 0.00326 -0.0833 0.8280 1.0000
0.250 0.4220 0.00868 0.00315 -0.0828 0.8072 1.0000
0.500 0.4477 0.00876 0.00309 -0.0819 0.7847 1.0000
0.750 0.4736 0.00888 0.00304 -0.0811 0.7626 1.0000
1.000 0.4985 0.00901 0.00303 -0.0802 0.7396 1.0000
1.250 0.5234 0.00916 0.00302 -0.0792 0.7171 1.0000
1.500 0.5477 0.00932 0.00306 -0.0782 0.6939 1.0000
1.750 0.5722 0.00951 0.00309 -0.0772 0.6719 1.0000
2.000 0.5963 0.00969 0.00316 -0.0762 0.6492 1.0000
2.250 0.6204 0.00990 0.00323 -0.0752 0.6277 1.0000
2.500 0.6444 0.01011 0.00334 -0.0742 0.6061 1.0000
2.750 0.6684 0.01033 0.00345 -0.0732 0.5854 1.0000
3.000 0.6924 0.01058 0.00357 -0.0723 0.5662 1.0000
3.250 0.7164 0.01081 0.00374 -0.0713 0.5463 1.0000
3.500 0.7404 0.01106 0.00391 -0.0704 0.5277 1.0000
3.750 0.7644 0.01133 0.00409 -0.0695 0.5100 1.0000
4.000 0.7884 0.01160 0.00429 -0.0686 0.4930 1.0000
4.250 0.8123 0.01189 0.00452 -0.0678 0.4762 1.0000
4.500 0.8363 0.01216 0.00476 -0.0669 0.4595 1.0000
4.750 0.8601 0.01244 0.00501 -0.0660 0.4430 1.0000
5.000 0.8839 0.01274 0.00527 -0.0651 0.4265 1.0000
5.250 0.9075 0.01304 0.00557 -0.0643 0.4104 1.0000
5.500 0.9310 0.01336 0.00587 -0.0634 0.3945 1.0000
5.750 0.9543 0.01369 0.00619 -0.0624 0.3784 1.0000
6.000 0.9774 0.01404 0.00652 -0.0615 0.3625 1.0000
6.250 1.0005 0.01442 0.00690 -0.0606 0.3470 1.0000
6.500 1.0232 0.01481 0.00727 -0.0596 0.3314 1.0000
6.750 1.0458 0.01522 0.00768 -0.0586 0.3161 1.0000
7.000 1.0678 0.01564 0.00808 -0.0576 0.3002 1.0000
7.250 1.0890 0.01600 0.00846 -0.0564 0.2810 1.0000
7.500 1.1102 0.01636 0.00883 -0.0553 0.2613 1.0000
7.750 1.1313 0.01680 0.00926 -0.0541 0.2446 1.0000
8.000 1.1521 0.01726 0.00973 -0.0530 0.2287 1.0000
8.250 1.1724 0.01776 0.01023 -0.0518 0.2126 1.0000
8.500 1.1929 0.01823 0.01076 -0.0507 0.1956 1.0000
8.750 1.2130 0.01873 0.01130 -0.0495 0.1759 1.0000
9.000 1.2315 0.01936 0.01191 -0.0482 0.1516 1.0000
9.250 1.2453 0.02044 0.01277 -0.0462 0.1056 1.0000
9.500 1.2495 0.02244 0.01438 -0.0430 0.0639 1.0000
9.750 1.2565 0.02407 0.01600 -0.0400 0.0520 1.0000
10.000 1.2627 0.02562 0.01757 -0.0371 0.0456 1.0000
10.250 1.2683 0.02705 0.01910 -0.0339 0.0417 1.0000
10.500 1.2734 0.02840 0.02054 -0.0308 0.0388 1.0000
10.750 1.2752 0.03004 0.02223 -0.0277 0.0367 1.0000
11.000 1.2718 0.03241 0.02462 -0.0243 0.0350 1.0000
11.250 1.2785 0.03404 0.02639 -0.0221 0.0338 1.0000
11.500 1.2852 0.03572 0.02821 -0.0201 0.0324 1.0000
11.750 1.2909 0.03750 0.03011 -0.0183 0.0308 1.0000
12.000 1.2958 0.03940 0.03210 -0.0167 0.0294 1.0000
12.250 1.3007 0.04156 0.03431 -0.0152 0.0284 1.0000
12.500 1.3078 0.04427 0.03707 -0.0135 0.0274 1.0000
12.750 1.3144 0.04746 0.04044 -0.0120 0.0267 1.0000
13.000 1.3156 0.04995 0.04316 -0.0106 0.0263 1.0000
13.250 1.3145 0.05273 0.04617 -0.0096 0.0259 1.0000
13.500 1.3110 0.05579 0.04946 -0.0088 0.0255 1.0000
13.750 1.3055 0.05916 0.05306 -0.0084 0.0250 1.0000
14.000 1.2981 0.06287 0.05699 -0.0084 0.0246 1.0000
14.250 1.2890 0.06692 0.06125 -0.0089 0.0242 1.0000
14.500 1.2782 0.07136 0.06591 -0.0099 0.0239 1.0000
14.750 1.2655 0.07628 0.07104 -0.0113 0.0237 1.0000
15.000 1.2506 0.08176 0.07673 -0.0133 0.0236 1.0000
15.250 1.2329 0.08790 0.08308 -0.0160 0.0236 1.0000
15.500 1.2132 0.09478 0.09019 -0.0194 0.0237 1.0000
15.750 1.1914 0.10247 0.09809 -0.0236 0.0238 1.0000
16.000 1.1677 0.11103 0.10685 -0.0286 0.0241 1.0000
16.250 1.1420 0.12063 0.11664 -0.0345 0.0245 1.0000
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