GOE 187 (SCHTTE-LANZ 2U10) AIRFOIL (goe187-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: GOE 187 (SCHTTE-LANZ 2U10) AIRFOIL (goe187-il) Reynolds number: 100,000 Max Cl/Cd: 58.22 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe187-il-100000-n5.txt Download as CSV file: xf-goe187-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 187 (SCHTTE-LANZ 2U10) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3076 0.10640 0.10180 -0.0253 1.0000 0.0244
-8.000 -0.3051 0.10407 0.09954 -0.0268 1.0000 0.0245
-7.750 -0.3032 0.10176 0.09732 -0.0282 1.0000 0.0245
-7.500 -0.2984 0.09924 0.09486 -0.0306 1.0000 0.0246
-7.250 -0.2932 0.09668 0.09237 -0.0328 1.0000 0.0247
-7.000 -0.2882 0.09415 0.08991 -0.0347 1.0000 0.0247
-6.750 -0.2836 0.09169 0.08751 -0.0362 1.0000 0.0248
-6.500 -0.2808 0.08942 0.08528 -0.0368 1.0000 0.0248
-6.250 -0.2680 0.08414 0.08008 -0.0388 0.9955 0.0252
-6.000 -0.2568 0.07868 0.07467 -0.0375 0.9896 0.0262
-5.750 -0.2310 0.07416 0.07010 -0.0424 0.9807 0.0273
-5.500 -0.2008 0.06972 0.06560 -0.0488 0.9709 0.0285
-5.250 -0.1680 0.06534 0.06114 -0.0555 0.9608 0.0299
-5.000 -0.1332 0.06106 0.05675 -0.0622 0.9506 0.0315
-4.750 -0.0918 0.05699 0.05249 -0.0697 0.9408 0.0338
-4.500 -0.0418 0.05434 0.04936 -0.0773 0.9290 0.0352
-4.250 -0.0135 0.04948 0.04441 -0.0805 0.9174 0.0359
-4.000 0.0099 0.04526 0.04018 -0.0824 0.9040 0.0376
-3.750 0.0403 0.04208 0.03680 -0.0846 0.8886 0.0400
-3.500 0.0735 0.03935 0.03375 -0.0866 0.8726 0.0433
-3.250 0.1085 0.03692 0.03081 -0.0882 0.8576 0.0478
-3.000 0.1317 0.03399 0.02784 -0.0888 0.8437 0.0529
-2.750 0.1603 0.03180 0.02533 -0.0896 0.8303 0.0652
-2.500 0.1902 0.03084 0.02389 -0.0901 0.8172 0.0877
-2.000 0.2556 0.02543 0.01769 -0.0888 0.7942 0.0310
-1.750 0.2862 0.02366 0.01547 -0.0883 0.7830 0.0279
-1.500 0.3166 0.02233 0.01362 -0.0876 0.7715 0.0260
-1.250 0.3444 0.02101 0.01208 -0.0874 0.7595 0.0280
-1.000 0.3728 0.01999 0.01079 -0.0869 0.7479 0.0303
-0.750 0.4011 0.01896 0.00950 -0.0863 0.7366 0.0307
-0.500 0.4289 0.01807 0.00839 -0.0856 0.7255 0.0318
-0.250 0.4561 0.01745 0.00760 -0.0849 0.7134 0.0359
0.000 0.4822 0.01664 0.00677 -0.0844 0.7013 0.0397
0.250 0.5091 0.01624 0.00618 -0.0839 0.6892 0.0455
0.500 0.5363 0.01587 0.00561 -0.0835 0.6768 0.0557
0.750 0.5643 0.01562 0.00520 -0.0832 0.6639 0.0758
1.000 0.5945 0.01347 0.00498 -0.0836 0.6508 1.0000
1.250 0.6212 0.01363 0.00483 -0.0832 0.6371 1.0000
1.500 0.6478 0.01380 0.00478 -0.0828 0.6233 1.0000
1.750 0.6742 0.01397 0.00476 -0.0824 0.6087 1.0000
2.000 0.7006 0.01415 0.00479 -0.0821 0.5933 1.0000
2.250 0.7268 0.01434 0.00484 -0.0817 0.5775 1.0000
2.500 0.7530 0.01454 0.00493 -0.0814 0.5616 1.0000
2.750 0.7791 0.01476 0.00504 -0.0811 0.5464 1.0000
3.000 0.8052 0.01500 0.00518 -0.0807 0.5319 1.0000
3.250 0.8311 0.01525 0.00536 -0.0804 0.5180 1.0000
3.500 0.8570 0.01552 0.00554 -0.0801 0.5048 1.0000
3.750 0.8828 0.01581 0.00575 -0.0798 0.4930 1.0000
4.000 0.9085 0.01612 0.00604 -0.0795 0.4813 1.0000
4.250 0.9340 0.01644 0.00632 -0.0791 0.4689 1.0000
4.500 0.9589 0.01677 0.00660 -0.0787 0.4552 1.0000
4.750 0.9836 0.01712 0.00690 -0.0782 0.4408 1.0000
5.000 1.0081 0.01749 0.00727 -0.0778 0.4270 1.0000
5.250 1.0327 0.01786 0.00764 -0.0773 0.4145 1.0000
5.500 1.0572 0.01825 0.00804 -0.0769 0.4036 1.0000
5.750 1.0816 0.01864 0.00851 -0.0765 0.3932 1.0000
6.000 1.1064 0.01903 0.00901 -0.0761 0.3840 1.0000
6.250 1.1308 0.01944 0.00949 -0.0757 0.3760 1.0000
6.500 1.1547 0.01984 0.01002 -0.0752 0.3651 1.0000
6.750 1.1784 0.02024 0.01061 -0.0747 0.3540 1.0000
7.000 1.2018 0.02067 0.01118 -0.0741 0.3439 1.0000
7.250 1.2246 0.02112 0.01175 -0.0735 0.3329 1.0000
7.500 1.2475 0.02155 0.01242 -0.0728 0.3211 1.0000
7.750 1.2697 0.02201 0.01315 -0.0721 0.3082 1.0000
8.000 1.2895 0.02250 0.01379 -0.0710 0.2852 1.0000
8.250 1.3030 0.02331 0.01439 -0.0692 0.2220 1.0000
8.500 1.3078 0.02517 0.01564 -0.0667 0.1570 1.0000
8.750 1.3173 0.02679 0.01705 -0.0647 0.1142 1.0000
9.000 1.3243 0.02855 0.01861 -0.0624 0.0866 1.0000
9.250 1.3241 0.03078 0.02052 -0.0594 0.0291 1.0000
9.500 1.3203 0.03298 0.02265 -0.0558 0.0201 1.0000
9.750 1.3206 0.03481 0.02466 -0.0527 0.0178 1.0000
10.000 1.3202 0.03685 0.02691 -0.0500 0.0164 1.0000
10.250 1.3179 0.03921 0.02949 -0.0477 0.0151 1.0000
10.500 1.3131 0.04200 0.03259 -0.0458 0.0140 1.0000
10.750 1.3075 0.04510 0.03592 -0.0445 0.0132 1.0000
11.000 1.3045 0.04811 0.03917 -0.0437 0.0127 1.0000
11.250 1.2995 0.05154 0.04283 -0.0432 0.0123 1.0000
11.500 1.2931 0.05530 0.04682 -0.0431 0.0120 1.0000
11.750 1.2857 0.05937 0.05110 -0.0434 0.0118 1.0000
12.000 1.2775 0.06366 0.05559 -0.0438 0.0116 1.0000
12.250 1.2689 0.06815 0.06028 -0.0445 0.0115 1.0000
12.500 1.2602 0.07274 0.06505 -0.0453 0.0113 1.0000
12.750 1.2517 0.07740 0.06988 -0.0462 0.0112 1.0000
13.000 1.2439 0.08203 0.07468 -0.0471 0.0111 1.0000
13.250 1.2371 0.08656 0.07936 -0.0480 0.0109 1.0000
13.500 1.2314 0.09099 0.08395 -0.0488 0.0107 1.0000
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Polar data table (+)
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