WASP (smoothed) (waspsm-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: WASP (smoothed) (waspsm-il) Reynolds number: 100,000 Max Cl/Cd: 50.99 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-waspsm-il-100000.txt Download as CSV file: xf-waspsm-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.4061 0.09687 0.09193 -0.0226 1.0000 0.1013
-8.000 -0.4284 0.09513 0.09037 -0.0277 1.0000 0.1035
-7.750 -0.4366 0.09086 0.08619 -0.0332 1.0000 0.1046
-7.500 -0.4125 0.08715 0.08245 -0.0248 1.0000 0.1077
-7.250 -0.4077 0.08425 0.07959 -0.0244 1.0000 0.1113
-7.000 -0.4123 0.08098 0.07642 -0.0287 1.0000 0.1165
-6.750 -0.4198 0.07613 0.07159 -0.0360 1.0000 0.1197
-6.500 -0.4081 0.07358 0.06910 -0.0307 1.0000 0.1225
-6.250 -0.4026 0.07074 0.06629 -0.0306 1.0000 0.1278
-6.000 -0.4055 0.06609 0.06157 -0.0363 1.0000 0.1350
-5.750 -0.3963 0.06419 0.05978 -0.0319 1.0000 0.1402
-5.500 -0.3942 0.06035 0.05584 -0.0348 1.0000 0.1505
-5.250 -0.3859 0.05830 0.05384 -0.0321 1.0000 0.1578
-5.000 -0.3796 0.05495 0.05043 -0.0327 1.0000 0.1672
-4.750 -0.3708 0.05198 0.04733 -0.0335 1.0000 0.1803
-4.500 -0.3602 0.04965 0.04503 -0.0315 1.0000 0.1868
-4.250 -0.3183 0.03090 0.02376 -0.0407 1.0000 0.0783
-4.000 -0.2992 0.02934 0.02211 -0.0398 1.0000 0.0821
-3.750 -0.2768 0.02698 0.01926 -0.0391 1.0000 0.0830
-3.500 -0.2527 0.02496 0.01677 -0.0384 1.0000 0.0843
-3.250 -0.2283 0.02379 0.01511 -0.0376 1.0000 0.0891
-3.000 -0.2040 0.02227 0.01350 -0.0374 1.0000 0.0945
-2.750 -0.1800 0.02132 0.01239 -0.0368 1.0000 0.1006
-2.500 -0.1570 0.02052 0.01157 -0.0364 1.0000 0.1106
-2.250 -0.1182 0.01963 0.01066 -0.0387 0.9959 0.1269
-2.000 -0.0701 0.01871 0.00986 -0.0429 0.9879 0.1600
-1.750 -0.0239 0.01763 0.00922 -0.0467 0.9792 0.2328
-1.500 0.0190 0.01605 0.00896 -0.0500 0.9708 0.4969
-1.250 0.0868 0.01465 0.00866 -0.0568 0.9665 1.0000
-1.000 0.1377 0.01471 0.00838 -0.0615 0.9545 1.0000
-0.750 0.1875 0.01472 0.00814 -0.0659 0.9421 1.0000
-0.500 0.2369 0.01465 0.00788 -0.0700 0.9294 1.0000
-0.250 0.2859 0.01452 0.00759 -0.0740 0.9163 1.0000
0.000 0.3313 0.01436 0.00731 -0.0770 0.9021 1.0000
0.250 0.3732 0.01419 0.00702 -0.0792 0.8865 1.0000
0.500 0.4118 0.01401 0.00675 -0.0806 0.8698 1.0000
0.750 0.4481 0.01384 0.00648 -0.0815 0.8523 1.0000
1.000 0.4797 0.01375 0.00630 -0.0815 0.8328 1.0000
1.250 0.5088 0.01373 0.00618 -0.0809 0.8115 1.0000
1.500 0.5390 0.01370 0.00604 -0.0806 0.7915 1.0000
1.750 0.5648 0.01380 0.00604 -0.0795 0.7684 1.0000
2.000 0.5923 0.01389 0.00600 -0.0787 0.7472 1.0000
2.250 0.6172 0.01407 0.00608 -0.0776 0.7243 1.0000
2.500 0.6433 0.01424 0.00614 -0.0767 0.7028 1.0000
2.750 0.6679 0.01447 0.00627 -0.0756 0.6808 1.0000
3.000 0.6928 0.01471 0.00640 -0.0745 0.6594 1.0000
3.250 0.7176 0.01497 0.00656 -0.0735 0.6388 1.0000
3.500 0.7415 0.01526 0.00680 -0.0724 0.6174 1.0000
3.750 0.7663 0.01556 0.00698 -0.0714 0.5977 1.0000
4.000 0.7902 0.01589 0.00725 -0.0703 0.5777 1.0000
4.250 0.8139 0.01624 0.00757 -0.0693 0.5577 1.0000
4.500 0.8382 0.01660 0.00786 -0.0683 0.5389 1.0000
4.750 0.8624 0.01700 0.00818 -0.0673 0.5206 1.0000
5.000 0.8854 0.01741 0.00860 -0.0662 0.5012 1.0000
5.250 0.9089 0.01784 0.00903 -0.0652 0.4827 1.0000
5.500 0.9326 0.01829 0.00943 -0.0642 0.4648 1.0000
5.750 0.9564 0.01877 0.00985 -0.0633 0.4475 1.0000
6.000 0.9792 0.01927 0.01037 -0.0622 0.4296 1.0000
6.250 1.0017 0.01979 0.01096 -0.0611 0.4117 1.0000
6.500 1.0244 0.02033 0.01152 -0.0601 0.3945 1.0000
6.750 1.0471 0.02090 0.01211 -0.0590 0.3779 1.0000
7.000 1.0697 0.02150 0.01273 -0.0580 0.3619 1.0000
7.250 1.0922 0.02212 0.01341 -0.0569 0.3463 1.0000
7.500 1.1143 0.02275 0.01408 -0.0558 0.3310 1.0000
7.750 1.1356 0.02327 0.01458 -0.0546 0.3144 1.0000
8.000 1.1538 0.02367 0.01505 -0.0529 0.2956 1.0000
8.250 1.1712 0.02401 0.01548 -0.0511 0.2762 1.0000
8.500 1.1888 0.02443 0.01596 -0.0494 0.2582 1.0000
8.750 1.2056 0.02492 0.01645 -0.0477 0.2402 1.0000
9.000 1.2200 0.02541 0.01715 -0.0456 0.2196 1.0000
9.250 1.2321 0.02599 0.01774 -0.0432 0.1964 1.0000
9.500 1.2397 0.02686 0.01868 -0.0404 0.1625 1.0000
9.750 1.2399 0.02864 0.02022 -0.0367 0.1206 1.0000
10.000 1.2408 0.03073 0.02214 -0.0333 0.0963 1.0000
10.250 1.2437 0.03263 0.02398 -0.0301 0.0830 1.0000
10.500 1.2462 0.03458 0.02588 -0.0270 0.0748 1.0000
10.750 1.2518 0.03646 0.02778 -0.0244 0.0686 1.0000
11.000 1.2615 0.03882 0.03012 -0.0223 0.0641 1.0000
11.250 1.2708 0.04083 0.03232 -0.0202 0.0599 1.0000
11.500 1.2818 0.04306 0.03447 -0.0188 0.0559 1.0000
11.750 1.2948 0.04595 0.03754 -0.0174 0.0532 1.0000
12.000 1.3026 0.04863 0.04053 -0.0155 0.0516 1.0000
12.250 1.3071 0.05155 0.04377 -0.0136 0.0503 1.0000
12.500 1.3076 0.05465 0.04714 -0.0117 0.0494 1.0000
12.750 1.3047 0.05782 0.05056 -0.0099 0.0485 1.0000
13.000 1.2979 0.06112 0.05409 -0.0085 0.0476 1.0000
13.250 1.2893 0.06463 0.05781 -0.0075 0.0468 1.0000
13.500 1.2803 0.06841 0.06177 -0.0070 0.0460 1.0000
13.750 1.2690 0.07272 0.06625 -0.0069 0.0455 1.0000
14.000 1.2519 0.07762 0.07139 -0.0076 0.0453 1.0000
14.250 1.2274 0.08338 0.07744 -0.0096 0.0456 1.0000
14.500 1.1669 0.09533 0.08996 -0.0171 0.0486 1.0000
14.750 1.1218 0.10714 0.10201 -0.0248 0.0508 1.0000
15.000 1.0840 0.11901 0.11402 -0.0325 0.0524 1.0000
15.250 1.0502 0.13139 0.12646 -0.0401 0.0536 1.0000
15.500 1.0272 0.14215 0.13722 -0.0459 0.0545 1.0000
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Polar data table (+)
Polar graphs
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