EH 2.0/10 (eh2010-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: EH 2.0/10 (eh2010-il) Reynolds number: 200,000 Max Cl/Cd: 63.3 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-eh2010-il-200000.txt Download as CSV file: xf-eh2010-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: EH 2.0/10
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 -0.5186 0.08790 0.08471 -0.0063 1.0000 0.0473
-8.500 -0.5232 0.08329 0.08016 -0.0096 1.0000 0.0492
-8.250 -0.5324 0.07831 0.07522 -0.0142 1.0000 0.0496
-8.000 -0.5448 0.07380 0.07070 -0.0167 1.0000 0.0505
-7.500 -0.5635 0.06547 0.06181 -0.0210 1.0000 0.0537
-7.250 -0.5689 0.05819 0.05442 -0.0211 1.0000 0.0546
-7.000 -0.5538 0.05498 0.05139 -0.0206 1.0000 0.0564
-6.750 -0.5408 0.05281 0.04919 -0.0199 1.0000 0.0593
-6.500 -0.5343 0.05195 0.04758 -0.0181 1.0000 0.0668
-6.000 -0.5232 0.03347 0.02835 -0.0140 1.0000 0.0381
-5.750 -0.5128 0.02847 0.02278 -0.0112 1.0000 0.0352
-5.500 -0.4981 0.02479 0.01855 -0.0086 1.0000 0.0345
-5.250 -0.4804 0.02259 0.01602 -0.0065 1.0000 0.0354
-5.000 -0.4626 0.02101 0.01420 -0.0046 1.0000 0.0374
-4.750 -0.4472 0.02023 0.01321 -0.0023 0.9998 0.0404
-4.500 -0.4039 0.01776 0.01052 -0.0055 0.9892 0.0451
-4.250 -0.3583 0.01674 0.00937 -0.0089 0.9760 0.0521
-4.000 -0.3165 0.01530 0.00791 -0.0117 0.9588 0.0602
-3.750 -0.2766 0.01432 0.00691 -0.0140 0.9376 0.0722
-3.500 -0.2428 0.01348 0.00606 -0.0149 0.9114 0.0878
-3.250 -0.2165 0.01292 0.00545 -0.0142 0.8825 0.1084
-3.000 -0.1942 0.01246 0.00499 -0.0127 0.8548 0.1349
-2.750 -0.1732 0.01193 0.00458 -0.0112 0.8296 0.1730
-2.500 -0.1543 0.01113 0.00418 -0.0095 0.8063 0.2685
-2.250 -0.1513 0.00922 0.00403 -0.0045 0.7870 0.6893
-2.000 -0.1292 0.00921 0.00431 -0.0014 0.7679 0.8361
-1.750 -0.1032 0.00946 0.00442 0.0003 0.7494 0.8841
-1.500 -0.0697 0.00981 0.00460 0.0005 0.7321 0.9146
-1.250 -0.0244 0.01025 0.00480 -0.0018 0.7148 0.9357
-1.000 0.0328 0.01068 0.00499 -0.0067 0.6959 0.9544
-0.750 0.0947 0.01099 0.00506 -0.0130 0.6776 0.9693
-0.500 0.1635 0.01108 0.00489 -0.0210 0.6598 0.9849
-0.250 0.2287 0.01085 0.00447 -0.0287 0.6414 0.9993
0.000 0.2530 0.01081 0.00432 -0.0284 0.6275 1.0000
0.250 0.2748 0.01081 0.00420 -0.0275 0.6146 1.0000
0.500 0.2968 0.01082 0.00409 -0.0267 0.6023 1.0000
0.750 0.3191 0.01083 0.00402 -0.0259 0.5897 1.0000
1.000 0.3414 0.01084 0.00397 -0.0251 0.5776 1.0000
1.250 0.3639 0.01088 0.00395 -0.0243 0.5659 1.0000
1.500 0.3865 0.01093 0.00392 -0.0234 0.5547 1.0000
1.750 0.4091 0.01099 0.00391 -0.0226 0.5443 1.0000
2.000 0.4318 0.01105 0.00391 -0.0218 0.5334 1.0000
2.250 0.4547 0.01111 0.00397 -0.0210 0.5224 1.0000
2.500 0.4776 0.01120 0.00401 -0.0202 0.5122 1.0000
2.750 0.5004 0.01131 0.00406 -0.0194 0.5025 1.0000
3.000 0.5233 0.01141 0.00414 -0.0185 0.4921 1.0000
3.250 0.5461 0.01153 0.00428 -0.0177 0.4818 1.0000
3.500 0.5688 0.01167 0.00439 -0.0168 0.4724 1.0000
3.750 0.5916 0.01182 0.00451 -0.0159 0.4629 1.0000
4.000 0.6144 0.01196 0.00469 -0.0151 0.4527 1.0000
4.250 0.6371 0.01214 0.00486 -0.0142 0.4433 1.0000
4.500 0.6598 0.01233 0.00504 -0.0133 0.4343 1.0000
4.750 0.6825 0.01250 0.00527 -0.0124 0.4240 1.0000
5.000 0.7053 0.01270 0.00550 -0.0115 0.4143 1.0000
5.250 0.7281 0.01294 0.00570 -0.0106 0.4054 1.0000
5.500 0.7508 0.01313 0.00599 -0.0097 0.3949 1.0000
5.750 0.7735 0.01336 0.00628 -0.0088 0.3849 1.0000
6.000 0.7963 0.01360 0.00654 -0.0079 0.3751 1.0000
6.250 0.8191 0.01384 0.00680 -0.0070 0.3649 1.0000
6.500 0.8418 0.01407 0.00713 -0.0061 0.3537 1.0000
6.750 0.8643 0.01431 0.00747 -0.0052 0.3421 1.0000
7.000 0.8864 0.01450 0.00771 -0.0042 0.3281 1.0000
7.250 0.9080 0.01466 0.00792 -0.0031 0.3121 1.0000
7.500 0.9293 0.01486 0.00814 -0.0021 0.2949 1.0000
7.750 0.9509 0.01505 0.00844 -0.0011 0.2744 1.0000
8.000 0.9716 0.01535 0.00875 -0.0001 0.2510 1.0000
8.250 0.9920 0.01574 0.00916 0.0009 0.2214 1.0000
8.500 1.0098 0.01644 0.00978 0.0021 0.1765 1.0000
8.750 1.0105 0.01900 0.01150 0.0049 0.0658 1.0000
9.000 1.0140 0.02126 0.01357 0.0077 0.0375 1.0000
9.250 1.0217 0.02290 0.01531 0.0101 0.0298 1.0000
9.500 1.0240 0.02478 0.01724 0.0127 0.0253 1.0000
9.750 1.0274 0.02644 0.01902 0.0153 0.0237 1.0000
10.000 1.0297 0.02794 0.02064 0.0181 0.0223 1.0000
10.250 1.0306 0.02956 0.02236 0.0207 0.0214 1.0000
10.500 1.0328 0.03136 0.02424 0.0227 0.0205 1.0000
10.750 1.0360 0.03333 0.02629 0.0242 0.0197 1.0000
11.000 1.0406 0.03541 0.02844 0.0255 0.0189 1.0000
11.250 1.0475 0.03758 0.03069 0.0267 0.0184 1.0000
11.500 1.0559 0.03988 0.03313 0.0278 0.0181 1.0000
11.750 1.0644 0.04237 0.03576 0.0288 0.0179 1.0000
12.000 1.0706 0.04543 0.03899 0.0297 0.0175 1.0000
12.250 1.0715 0.04908 0.04286 0.0303 0.0171 1.0000
13.000 1.0451 0.06062 0.05509 0.0285 0.0164 1.0000
13.250 1.0358 0.06451 0.05918 0.0268 0.0161 1.0000
13.500 1.0238 0.06965 0.06452 0.0250 0.0163 1.0000
13.750 0.9269 0.06961 0.06486 0.0245 0.0174 1.0000
14.000 0.9105 0.07574 0.07118 0.0221 0.0174 1.0000
14.250 0.8952 0.08167 0.07729 0.0192 0.0176 1.0000
14.500 0.8768 0.08830 0.08409 0.0160 0.0175 1.0000
14.750 0.8570 0.09527 0.09127 0.0120 0.0179 1.0000
15.000 0.8087 0.10795 0.10437 0.0040 0.0198 1.0000
15.250 0.7660 0.11874 0.11536 -0.0033 0.0211 1.0000
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Polar data table (+)
Polar graphs
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