EPPLER 593 AIRFOIL (e593-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 593 AIRFOIL (e593-il) Reynolds number: 1,000,000 Max Cl/Cd: 148.09 at α=8.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e593-il-1000000.txt Download as CSV file: xf-e593-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 593 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3171 0.08909 0.08603 0.0046 0.4743 0.0129
-8.500 -0.3162 0.08437 0.08132 0.0027 0.4734 0.0129
-8.250 -0.3158 0.07968 0.07665 0.0008 0.4724 0.0129
-8.000 -0.3200 0.07459 0.07157 -0.0009 0.4716 0.0132
-7.750 -0.3182 0.07103 0.06801 -0.0022 0.4703 0.0133
-7.500 -0.4977 0.03050 0.02647 -0.0375 0.4785 0.0079
-7.250 -0.4828 0.02638 0.02202 -0.0379 0.4771 0.0075
-7.000 -0.4668 0.02193 0.01701 -0.0380 0.4756 0.0072
-6.750 -0.4453 0.01934 0.01400 -0.0376 0.4740 0.0069
-6.500 -0.4215 0.01752 0.01185 -0.0371 0.4723 0.0068
-6.250 -0.3963 0.01619 0.01027 -0.0367 0.4704 0.0067
-6.000 -0.3703 0.01518 0.00905 -0.0363 0.4683 0.0066
-5.750 -0.3438 0.01438 0.00808 -0.0359 0.4656 0.0066
-5.500 -0.3168 0.01364 0.00722 -0.0356 0.4644 0.0067
-5.250 -0.2896 0.01303 0.00650 -0.0352 0.4631 0.0067
-5.000 -0.2621 0.01249 0.00587 -0.0350 0.4616 0.0068
-4.750 -0.2344 0.01201 0.00531 -0.0347 0.4601 0.0070
-4.500 -0.2065 0.01159 0.00481 -0.0344 0.4585 0.0071
-4.250 -0.1785 0.01122 0.00436 -0.0342 0.4569 0.0074
-4.000 -0.1504 0.01091 0.00399 -0.0340 0.4553 0.0077
-3.750 -0.1225 0.01049 0.00350 -0.0337 0.4536 0.0088
-3.500 -0.0945 0.01022 0.00316 -0.0334 0.4515 0.0110
-3.250 -0.0667 0.00988 0.00287 -0.0332 0.4494 0.0237
-3.000 -0.0384 0.00967 0.00270 -0.0331 0.4485 0.0326
-2.750 -0.0100 0.00951 0.00257 -0.0330 0.4473 0.0399
-2.500 0.0185 0.00937 0.00246 -0.0329 0.4460 0.0475
-2.250 0.0469 0.00925 0.00236 -0.0328 0.4447 0.0559
-2.000 0.0754 0.00914 0.00228 -0.0327 0.4432 0.0669
-1.750 0.1039 0.00904 0.00221 -0.0326 0.4418 0.0776
-1.500 0.1324 0.00895 0.00214 -0.0325 0.4403 0.0882
-1.250 0.1610 0.00889 0.00207 -0.0324 0.4387 0.0973
-1.000 0.1895 0.00884 0.00202 -0.0324 0.4370 0.1081
-0.750 0.2178 0.00882 0.00202 -0.0323 0.4350 0.1207
-0.500 0.2463 0.00878 0.00200 -0.0322 0.4337 0.1341
-0.250 0.2749 0.00869 0.00197 -0.0322 0.4328 0.1501
0.000 0.3035 0.00861 0.00194 -0.0322 0.4317 0.1706
0.250 0.3320 0.00851 0.00193 -0.0321 0.4304 0.2017
0.500 0.3603 0.00838 0.00193 -0.0321 0.4290 0.2475
0.750 0.3884 0.00820 0.00193 -0.0321 0.4275 0.3133
1.000 0.4146 0.00763 0.00195 -0.0319 0.4260 0.5303
1.250 0.4435 0.00649 0.00202 -0.0318 0.4247 0.9726
1.500 0.4949 0.00653 0.00200 -0.0368 0.4231 1.0000
1.750 0.5221 0.00662 0.00204 -0.0364 0.4215 1.0000
2.000 0.5491 0.00677 0.00213 -0.0361 0.4194 1.0000
2.250 0.5765 0.00682 0.00217 -0.0359 0.4183 1.0000
2.500 0.6039 0.00687 0.00220 -0.0356 0.4171 1.0000
2.750 0.6314 0.00692 0.00225 -0.0354 0.4159 1.0000
3.000 0.6590 0.00697 0.00229 -0.0352 0.4143 1.0000
3.250 0.6865 0.00702 0.00233 -0.0350 0.4127 1.0000
3.500 0.7142 0.00708 0.00237 -0.0348 0.4110 1.0000
3.750 0.7418 0.00713 0.00241 -0.0347 0.4093 1.0000
4.000 0.7695 0.00720 0.00246 -0.0345 0.4071 1.0000
4.250 0.7968 0.00737 0.00259 -0.0343 0.4042 1.0000
4.500 0.8248 0.00739 0.00263 -0.0343 0.4027 1.0000
4.750 0.8527 0.00742 0.00268 -0.0342 0.4008 1.0000
5.000 0.8806 0.00746 0.00274 -0.0341 0.3985 1.0000
5.250 0.9085 0.00750 0.00279 -0.0341 0.3962 1.0000
5.500 0.9364 0.00756 0.00284 -0.0340 0.3937 1.0000
5.750 0.9639 0.00768 0.00294 -0.0339 0.3905 1.0000
6.000 0.9919 0.00773 0.00303 -0.0339 0.3881 1.0000
6.250 1.0199 0.00777 0.00311 -0.0339 0.3855 1.0000
6.500 1.0478 0.00782 0.00320 -0.0339 0.3825 1.0000
6.750 1.0756 0.00789 0.00327 -0.0339 0.3794 1.0000
7.000 1.1030 0.00803 0.00339 -0.0339 0.3755 1.0000
7.250 1.1311 0.00805 0.00349 -0.0339 0.3719 1.0000
7.500 1.1590 0.00811 0.00358 -0.0340 0.3672 1.0000
7.750 1.1864 0.00823 0.00370 -0.0340 0.3623 1.0000
8.000 1.2141 0.00832 0.00384 -0.0340 0.3574 1.0000
8.250 1.2416 0.00843 0.00397 -0.0340 0.3509 1.0000
8.500 1.2689 0.00857 0.00413 -0.0340 0.3441 1.0000
8.750 1.2958 0.00875 0.00431 -0.0340 0.3341 1.0000
9.000 1.3225 0.00896 0.00452 -0.0340 0.3219 1.0000
9.250 1.3484 0.00928 0.00481 -0.0340 0.3056 1.0000
9.500 1.3733 0.00973 0.00519 -0.0339 0.2824 1.0000
9.750 1.3963 0.01044 0.00577 -0.0337 0.2530 1.0000
10.000 1.4184 0.01123 0.00643 -0.0334 0.2256 1.0000
10.250 1.4402 0.01202 0.00712 -0.0331 0.2015 1.0000
10.500 1.4608 0.01290 0.00788 -0.0327 0.1779 1.0000
10.750 1.4804 0.01382 0.00870 -0.0322 0.1550 1.0000
11.000 1.4999 0.01469 0.00950 -0.0317 0.1371 1.0000
11.250 1.5185 0.01557 0.01033 -0.0312 0.1214 1.0000
11.500 1.5358 0.01651 0.01122 -0.0306 0.1076 1.0000
11.750 1.5508 0.01757 0.01223 -0.0298 0.0944 1.0000
12.000 1.5640 0.01867 0.01331 -0.0288 0.0839 1.0000
12.250 1.5716 0.02008 0.01469 -0.0276 0.0730 1.0000
12.500 1.5716 0.02170 0.01634 -0.0257 0.0673 1.0000
12.750 1.5595 0.02516 0.01993 -0.0259 0.0644 1.0000
13.000 1.5544 0.02869 0.02354 -0.0268 0.0617 1.0000
13.250 1.5394 0.03294 0.02781 -0.0272 0.0566 1.0000
13.500 1.5298 0.03647 0.03139 -0.0273 0.0528 1.0000
13.750 1.5166 0.04032 0.03527 -0.0274 0.0493 1.0000
14.000 1.5076 0.04375 0.03874 -0.0275 0.0457 1.0000
14.250 1.4997 0.04709 0.04212 -0.0276 0.0431 1.0000
14.500 1.4897 0.05068 0.04572 -0.0279 0.0398 1.0000
14.750 1.4831 0.05404 0.04912 -0.0282 0.0363 1.0000
15.000 1.4811 0.05704 0.05217 -0.0286 0.0349 1.0000
15.250 1.4766 0.06048 0.05565 -0.0292 0.0322 1.0000
15.500 1.4749 0.06361 0.05880 -0.0298 0.0295 1.0000
15.750 1.4699 0.06725 0.06248 -0.0305 0.0270 1.0000
16.000 1.4708 0.07018 0.06546 -0.0311 0.0255 1.0000
16.250 1.4652 0.07403 0.06932 -0.0321 0.0226 1.0000
16.500 1.4657 0.07715 0.07249 -0.0328 0.0214 1.0000
16.750 1.4633 0.08071 0.07610 -0.0338 0.0196 1.0000
17.000 1.4605 0.08435 0.07977 -0.0349 0.0180 1.0000
17.250 1.4594 0.08787 0.08336 -0.0359 0.0169 1.0000
17.500 1.4576 0.09154 0.08706 -0.0371 0.0155 1.0000
17.750 1.4533 0.09562 0.09119 -0.0385 0.0143 1.0000
18.000 1.4533 0.09910 0.09475 -0.0397 0.0136 1.0000
18.250 1.4506 0.10307 0.09878 -0.0412 0.0127 1.0000
18.500 1.4475 0.10717 0.10293 -0.0428 0.0118 1.0000
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