EH 1.5/9.0 (eh1590-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: EH 1.5/9.0 (eh1590-il) Reynolds number: 200,000 Max Cl/Cd: 60.25 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-eh1590-il-200000.txt Download as CSV file: xf-eh1590-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: EH 1.5/9.0
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
------ -------- --------- --------- -------- -------- --------
-7.250 -0.5896 0.06357 0.05967 -0.0182 1.0000 0.0531
-7.000 -0.5883 0.05581 0.05197 -0.0188 1.0000 0.0545
-6.750 -0.5756 0.05250 0.04868 -0.0183 1.0000 0.0558
-6.500 -0.5632 0.04947 0.04558 -0.0178 1.0000 0.0576
-5.750 -0.5283 0.03216 0.02681 -0.0129 1.0000 0.0361
-5.500 -0.5102 0.02727 0.02094 -0.0097 1.0000 0.0297
-5.250 -0.4896 0.02492 0.01825 -0.0082 1.0000 0.0295
-5.000 -0.4710 0.02124 0.01415 -0.0067 1.0000 0.0307
-4.750 -0.4496 0.01983 0.01268 -0.0057 1.0000 0.0336
-4.500 -0.4269 0.01817 0.01080 -0.0043 1.0000 0.0346
-4.250 -0.4047 0.01680 0.00930 -0.0029 1.0000 0.0361
-4.000 -0.3834 0.01568 0.00809 -0.0013 1.0000 0.0392
-3.750 -0.3653 0.01438 0.00678 0.0006 1.0000 0.0440
-3.500 -0.3478 0.01370 0.00613 0.0024 1.0000 0.0553
-3.250 -0.3250 0.01299 0.00551 0.0030 0.9973 0.0778
-3.000 -0.2811 0.01202 0.00478 -0.0008 0.9855 0.1295
-2.750 -0.2396 0.01091 0.00421 -0.0042 0.9725 0.2335
-2.500 -0.2146 0.00874 0.00393 -0.0043 0.9554 0.6531
-2.250 -0.1840 0.00847 0.00418 -0.0030 0.9366 0.8306
-2.000 -0.1484 0.00861 0.00425 -0.0030 0.9165 0.8865
-1.750 -0.1105 0.00884 0.00434 -0.0036 0.8942 0.9177
-1.500 -0.0698 0.00909 0.00439 -0.0049 0.8707 0.9382
-1.250 -0.0212 0.00933 0.00439 -0.0082 0.8458 0.9533
-1.000 0.0314 0.00952 0.00436 -0.0125 0.8199 0.9659
-0.750 0.1009 0.00968 0.00427 -0.0204 0.7934 0.9852
-0.500 0.1633 0.00953 0.00388 -0.0274 0.7660 1.0000
-0.250 0.1835 0.00952 0.00372 -0.0261 0.7423 1.0000
0.000 0.2041 0.00953 0.00357 -0.0249 0.7204 1.0000
0.250 0.2254 0.00955 0.00346 -0.0238 0.6997 1.0000
0.500 0.2469 0.00958 0.00336 -0.0227 0.6805 1.0000
0.750 0.2686 0.00962 0.00327 -0.0217 0.6630 1.0000
1.000 0.2908 0.00966 0.00323 -0.0208 0.6450 1.0000
1.250 0.3132 0.00971 0.00320 -0.0198 0.6282 1.0000
1.500 0.3358 0.00978 0.00318 -0.0189 0.6120 1.0000
1.750 0.3585 0.00986 0.00318 -0.0180 0.5967 1.0000
2.000 0.3813 0.00995 0.00320 -0.0171 0.5817 1.0000
2.250 0.4042 0.01005 0.00324 -0.0162 0.5670 1.0000
2.500 0.4271 0.01017 0.00333 -0.0153 0.5526 1.0000
2.750 0.4500 0.01030 0.00341 -0.0144 0.5386 1.0000
3.000 0.4731 0.01044 0.00351 -0.0136 0.5245 1.0000
3.250 0.4962 0.01058 0.00363 -0.0127 0.5106 1.0000
3.500 0.5194 0.01074 0.00377 -0.0118 0.4968 1.0000
3.750 0.5426 0.01091 0.00396 -0.0110 0.4830 1.0000
4.000 0.5658 0.01109 0.00413 -0.0101 0.4693 1.0000
4.250 0.5891 0.01128 0.00432 -0.0093 0.4554 1.0000
4.500 0.6125 0.01148 0.00453 -0.0084 0.4414 1.0000
4.750 0.6359 0.01169 0.00478 -0.0076 0.4272 1.0000
5.000 0.6593 0.01190 0.00502 -0.0067 0.4126 1.0000
5.250 0.6827 0.01211 0.00528 -0.0059 0.3969 1.0000
5.500 0.7061 0.01232 0.00556 -0.0051 0.3807 1.0000
5.750 0.7294 0.01254 0.00583 -0.0042 0.3635 1.0000
6.000 0.7519 0.01270 0.00601 -0.0033 0.3387 1.0000
6.250 0.7736 0.01289 0.00616 -0.0023 0.3019 1.0000
6.500 0.7959 0.01321 0.00646 -0.0014 0.2660 1.0000
6.750 0.8170 0.01373 0.00686 -0.0005 0.2178 1.0000
7.000 0.8273 0.01585 0.00807 0.0013 0.0716 1.0000
7.250 0.8399 0.01788 0.00990 0.0034 0.0387 1.0000
7.500 0.8576 0.01903 0.01114 0.0048 0.0315 1.0000
7.750 0.8705 0.02077 0.01298 0.0067 0.0287 1.0000
8.000 0.8873 0.02211 0.01447 0.0084 0.0269 1.0000
8.250 0.9037 0.02365 0.01612 0.0100 0.0255 1.0000
8.500 0.9210 0.02513 0.01769 0.0114 0.0236 1.0000
8.750 0.9366 0.02686 0.01943 0.0126 0.0213 1.0000
9.000 0.9525 0.02996 0.02267 0.0139 0.0203 1.0000
9.250 0.9685 0.03333 0.02630 0.0151 0.0200 1.0000
9.500 0.9821 0.03667 0.02995 0.0165 0.0200 1.0000
9.750 0.9946 0.03936 0.03291 0.0179 0.0201 1.0000
10.000 1.0059 0.04163 0.03545 0.0193 0.0204 1.0000
10.250 1.0145 0.04365 0.03777 0.0211 0.0209 1.0000
10.500 1.0079 0.04731 0.04207 0.0240 0.0229 1.0000
10.750 0.9869 0.05180 0.04700 0.0270 0.0246 1.0000
11.000 0.9684 0.05572 0.05116 0.0283 0.0256 1.0000
11.250 0.9505 0.05982 0.05546 0.0279 0.0261 1.0000
11.500 0.9326 0.06444 0.06025 0.0261 0.0266 1.0000
11.750 0.9122 0.06999 0.06597 0.0230 0.0269 1.0000
12.000 0.8916 0.07629 0.07241 0.0188 0.0272 1.0000
12.250 0.8719 0.08302 0.07926 0.0137 0.0271 1.0000
12.500 0.8510 0.09085 0.08721 0.0078 0.0270 1.0000
12.750 0.8273 0.10040 0.09685 0.0010 0.0272 1.0000
13.000 0.8044 0.11103 0.10753 -0.0060 0.0273 1.0000
13.250 0.6816 0.11564 0.11244 -0.0069 0.0261 1.0000
|
Polar data table (+)
Polar graphs
<< Back to EH 1.5/9.0 (eh1590-il)