EPPLER 598 AIRFOIL (e598-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 598 AIRFOIL (e598-il) Reynolds number: 1,000,000 Max Cl/Cd: 137.2 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e598-il-1000000.txt Download as CSV file: xf-e598-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 598 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3030 0.09340 0.09074 -0.0033 0.5988 0.0125
-9.000 -0.3017 0.08854 0.08589 -0.0053 0.5950 0.0126
-8.750 -0.3015 0.08411 0.08146 -0.0067 0.5906 0.0128
-8.500 -0.2963 0.08094 0.07827 -0.0078 0.5857 0.0129
-8.250 -0.2918 0.07758 0.07489 -0.0091 0.5814 0.0131
-8.000 -0.2888 0.07395 0.07127 -0.0104 0.5776 0.0132
-7.750 -0.4985 0.03014 0.02663 -0.0454 0.6062 0.0082
-7.500 -0.4824 0.02642 0.02250 -0.0456 0.5999 0.0075
-7.250 -0.4687 0.02200 0.01753 -0.0454 0.5947 0.0073
-7.000 -0.4486 0.01939 0.01450 -0.0449 0.5886 0.0071
-6.750 -0.4258 0.01756 0.01232 -0.0443 0.5824 0.0069
-6.500 -0.4014 0.01616 0.01068 -0.0438 0.5774 0.0068
-6.250 -0.3760 0.01507 0.00937 -0.0434 0.5719 0.0068
-6.000 -0.3501 0.01420 0.00831 -0.0430 0.5662 0.0068
-5.750 -0.3236 0.01344 0.00742 -0.0426 0.5616 0.0068
-5.500 -0.2967 0.01279 0.00665 -0.0422 0.5565 0.0069
-5.250 -0.2697 0.01223 0.00597 -0.0419 0.5518 0.0070
-5.000 -0.2423 0.01175 0.00538 -0.0416 0.5474 0.0071
-4.750 -0.2147 0.01129 0.00484 -0.0414 0.5431 0.0073
-4.500 -0.1870 0.01091 0.00438 -0.0411 0.5386 0.0075
-4.250 -0.1592 0.01056 0.00393 -0.0409 0.5343 0.0079
-4.000 -0.1315 0.01013 0.00344 -0.0406 0.5307 0.0089
-3.750 -0.1034 0.00979 0.00306 -0.0404 0.5268 0.0109
-3.500 -0.0757 0.00941 0.00270 -0.0402 0.5227 0.0193
-3.250 -0.0478 0.00919 0.00249 -0.0400 0.5188 0.0300
-3.000 -0.0196 0.00904 0.00235 -0.0399 0.5152 0.0377
-2.750 0.0088 0.00888 0.00222 -0.0398 0.5117 0.0451
-2.500 0.0372 0.00876 0.00211 -0.0398 0.5080 0.0527
-2.250 0.0655 0.00865 0.00201 -0.0397 0.5043 0.0620
-2.000 0.0937 0.00859 0.00196 -0.0396 0.5002 0.0734
-1.750 0.1223 0.00847 0.00188 -0.0396 0.4973 0.0836
-1.500 0.1508 0.00838 0.00180 -0.0395 0.4939 0.0929
-1.250 0.1794 0.00832 0.00173 -0.0395 0.4903 0.1018
-1.000 0.2077 0.00825 0.00167 -0.0394 0.4865 0.1144
-0.750 0.2361 0.00818 0.00162 -0.0394 0.4830 0.1276
-0.500 0.2647 0.00809 0.00157 -0.0394 0.4799 0.1420
-0.250 0.2932 0.00801 0.00153 -0.0393 0.4764 0.1601
0.000 0.3215 0.00794 0.00150 -0.0393 0.4726 0.1842
0.250 0.3495 0.00787 0.00150 -0.0393 0.4685 0.2216
0.500 0.3777 0.00771 0.00150 -0.0393 0.4657 0.2767
0.750 0.4053 0.00744 0.00150 -0.0392 0.4622 0.3714
1.000 0.4263 0.00640 0.00153 -0.0381 0.4587 0.7487
1.250 0.4737 0.00597 0.00161 -0.0418 0.4542 0.9881
1.500 0.5270 0.00600 0.00159 -0.0472 0.4499 1.0000
1.750 0.5540 0.00604 0.00160 -0.0469 0.4464 1.0000
2.000 0.5809 0.00610 0.00162 -0.0465 0.4423 1.0000
2.250 0.6077 0.00619 0.00165 -0.0462 0.4381 1.0000
2.500 0.6347 0.00625 0.00169 -0.0459 0.4345 1.0000
2.750 0.6618 0.00629 0.00172 -0.0456 0.4305 1.0000
3.000 0.6887 0.00637 0.00177 -0.0454 0.4262 1.0000
3.250 0.7155 0.00649 0.00183 -0.0451 0.4215 1.0000
3.500 0.7427 0.00653 0.00188 -0.0449 0.4178 1.0000
3.750 0.7698 0.00660 0.00194 -0.0446 0.4132 1.0000
4.000 0.7966 0.00671 0.00202 -0.0444 0.4084 1.0000
4.250 0.8236 0.00681 0.00210 -0.0442 0.4040 1.0000
4.500 0.8507 0.00688 0.00217 -0.0440 0.3993 1.0000
4.750 0.8776 0.00699 0.00227 -0.0437 0.3940 1.0000
5.000 0.9044 0.00711 0.00237 -0.0435 0.3891 1.0000
5.250 0.9315 0.00720 0.00246 -0.0434 0.3839 1.0000
5.500 0.9582 0.00733 0.00258 -0.0432 0.3780 1.0000
5.750 0.9851 0.00745 0.00270 -0.0430 0.3724 1.0000
6.000 1.0120 0.00757 0.00281 -0.0428 0.3660 1.0000
6.250 1.0386 0.00774 0.00296 -0.0427 0.3594 1.0000
6.500 1.0655 0.00785 0.00309 -0.0425 0.3527 1.0000
6.750 1.0919 0.00805 0.00326 -0.0424 0.3453 1.0000
7.000 1.1188 0.00818 0.00341 -0.0423 0.3387 1.0000
7.250 1.1450 0.00840 0.00360 -0.0421 0.3305 1.0000
7.500 1.1717 0.00854 0.00376 -0.0420 0.3231 1.0000
7.750 1.1978 0.00878 0.00398 -0.0418 0.3145 1.0000
8.000 1.2240 0.00898 0.00418 -0.0417 0.3053 1.0000
8.250 1.2499 0.00922 0.00441 -0.0416 0.2962 1.0000
8.500 1.2753 0.00951 0.00468 -0.0414 0.2857 1.0000
8.750 1.3009 0.00978 0.00494 -0.0412 0.2748 1.0000
9.000 1.3259 0.01009 0.00523 -0.0410 0.2630 1.0000
9.250 1.3505 0.01044 0.00555 -0.0407 0.2507 1.0000
9.500 1.3744 0.01085 0.00592 -0.0404 0.2359 1.0000
9.750 1.3976 0.01130 0.00633 -0.0401 0.2207 1.0000
10.000 1.4203 0.01179 0.00677 -0.0396 0.2056 1.0000
10.250 1.4419 0.01236 0.00727 -0.0391 0.1892 1.0000
10.500 1.4621 0.01302 0.00785 -0.0384 0.1718 1.0000
10.750 1.4814 0.01371 0.00847 -0.0377 0.1540 1.0000
11.000 1.4988 0.01450 0.00917 -0.0367 0.1358 1.0000
11.250 1.5144 0.01535 0.00994 -0.0355 0.1201 1.0000
11.750 1.5399 0.01716 0.01165 -0.0326 0.0930 1.0000
12.250 1.5467 0.01925 0.01370 -0.0272 0.0746 1.0000
12.500 1.5435 0.02089 0.01532 -0.0249 0.0662 1.0000
12.750 1.5420 0.02286 0.01730 -0.0237 0.0590 1.0000
13.250 1.5433 0.02722 0.02172 -0.0225 0.0492 1.0000
13.750 1.5423 0.03217 0.02675 -0.0219 0.0418 1.0000
14.000 1.5395 0.03496 0.02957 -0.0217 0.0387 1.0000
14.250 1.5377 0.03767 0.03233 -0.0215 0.0357 1.0000
14.500 1.5319 0.04083 0.03552 -0.0215 0.0324 1.0000
14.750 1.5293 0.04369 0.03844 -0.0215 0.0303 1.0000
15.250 1.5191 0.05011 0.04496 -0.0219 0.0260 1.0000
15.500 1.5143 0.05349 0.04840 -0.0223 0.0243 1.0000
15.750 1.5100 0.05691 0.05187 -0.0228 0.0227 1.0000
16.000 1.5067 0.06028 0.05531 -0.0234 0.0213 1.0000
16.250 1.5017 0.06397 0.05905 -0.0241 0.0200 1.0000
16.500 1.4985 0.06748 0.06263 -0.0249 0.0187 1.0000
16.750 1.4940 0.07126 0.06647 -0.0258 0.0175 1.0000
17.000 1.4880 0.07535 0.07062 -0.0270 0.0164 1.0000
17.250 1.4849 0.07905 0.07439 -0.0280 0.0154 1.0000
17.500 1.4802 0.08309 0.07850 -0.0292 0.0144 1.0000
17.750 1.4739 0.08745 0.08293 -0.0307 0.0137 1.0000
18.000 1.4687 0.09172 0.08728 -0.0321 0.0130 1.0000
18.250 1.4653 0.09573 0.09136 -0.0335 0.0121 1.0000
18.500 1.4592 0.10029 0.09599 -0.0353 0.0115 1.0000
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Polar data table (+)
Polar graphs
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