EPPLER 1233 AIRFOIL (e1233-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 1233 AIRFOIL (e1233-il) Reynolds number: 50,000 Max Cl/Cd: 21.16 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e1233-il-50000-n5.txt Download as CSV file: xf-e1233-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 1233 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.3340 0.10281 0.09620 -0.0545 1.0000 0.0540
-10.500 -0.3520 0.09674 0.09023 -0.0562 1.0000 0.0537
-10.250 -0.3788 0.08989 0.08345 -0.0585 1.0000 0.0532
-10.000 -0.4141 0.08371 0.07732 -0.0600 1.0000 0.0526
-9.750 -0.4543 0.07890 0.07255 -0.0599 1.0000 0.0519
-9.500 -0.4976 0.07534 0.06901 -0.0580 0.9998 0.0513
-9.250 -0.5193 0.06898 0.06234 -0.0638 0.9854 0.0510
-9.000 -0.5280 0.06382 0.05681 -0.0671 0.9711 0.0513
-8.750 -0.5286 0.05947 0.05209 -0.0688 0.9556 0.0521
-8.500 -0.5256 0.05516 0.04728 -0.0699 0.9406 0.0536
-8.250 -0.5146 0.05151 0.04315 -0.0707 0.9271 0.0553
-8.000 -0.4897 0.04955 0.04110 -0.0721 0.9160 0.0579
-7.750 -0.4670 0.04652 0.03761 -0.0733 0.9052 0.0606
-7.500 -0.4454 0.04419 0.03498 -0.0734 0.8926 0.0631
-7.250 -0.4180 0.04246 0.03310 -0.0743 0.8817 0.0673
-7.000 -0.3857 0.04051 0.03094 -0.0756 0.8724 0.0726
-6.750 -0.3588 0.03889 0.02903 -0.0756 0.8605 0.0787
-6.500 -0.3201 0.03729 0.02740 -0.0776 0.8533 0.0872
-6.250 -0.2943 0.03615 0.02624 -0.0774 0.8407 0.0962
-6.000 -0.2522 0.03465 0.02462 -0.0796 0.8340 0.1113
-5.750 -0.2269 0.03372 0.02366 -0.0792 0.8208 0.1254
-5.500 -0.1936 0.03260 0.02254 -0.0802 0.8108 0.1441
-5.250 -0.1614 0.03149 0.02149 -0.0810 0.8002 0.1651
-5.000 -0.1360 0.03058 0.02062 -0.0808 0.7881 0.1881
-4.750 -0.1034 0.02935 0.01951 -0.0819 0.7790 0.2200
-4.500 -0.0862 0.02850 0.01884 -0.0805 0.7654 0.2545
-4.250 -0.0639 0.02733 0.01803 -0.0801 0.7548 0.3147
-4.000 -0.0460 0.02649 0.01788 -0.0781 0.7434 0.4161
-3.750 -0.0252 0.02698 0.01886 -0.0742 0.7318 0.5282
-3.500 0.0062 0.02751 0.01924 -0.0728 0.7219 0.5993
-3.250 0.0232 0.02806 0.01960 -0.0699 0.7093 0.6385
-3.000 0.0544 0.02863 0.01990 -0.0687 0.7002 0.6715
-2.750 0.0696 0.02906 0.02015 -0.0657 0.6880 0.6980
-2.500 0.0959 0.02963 0.02051 -0.0636 0.6781 0.7205
-2.250 0.1191 0.03014 0.02085 -0.0611 0.6678 0.7421
-2.000 0.1435 0.03057 0.02110 -0.0589 0.6582 0.7634
-1.750 0.1688 0.03087 0.02122 -0.0571 0.6484 0.7829
-1.500 0.1931 0.03104 0.02121 -0.0556 0.6391 0.7994
-1.250 0.2142 0.03106 0.02107 -0.0541 0.6299 0.8136
-1.000 0.2418 0.03105 0.02086 -0.0538 0.6215 0.8247
-0.750 0.2626 0.03106 0.02075 -0.0526 0.6122 0.8343
-0.500 0.2913 0.03091 0.02037 -0.0528 0.6049 0.8439
-0.250 0.3063 0.03102 0.02043 -0.0508 0.5954 0.8520
0.000 0.3375 0.03087 0.02006 -0.0516 0.5886 0.8597
0.250 0.3486 0.03101 0.02016 -0.0491 0.5800 0.8677
0.500 0.3740 0.03098 0.01999 -0.0490 0.5726 0.8745
0.750 0.3953 0.03095 0.01982 -0.0482 0.5662 0.8818
1.000 0.4107 0.03119 0.02003 -0.0467 0.5578 0.8885
1.250 0.4362 0.03112 0.01981 -0.0466 0.5519 0.8954
1.500 0.4548 0.03137 0.02001 -0.0456 0.5447 0.9016
1.750 0.4715 0.03158 0.02019 -0.0443 0.5376 0.9087
2.000 0.5041 0.03154 0.01998 -0.0454 0.5324 0.9144
2.250 0.5179 0.03202 0.02049 -0.0440 0.5253 0.9214
2.500 0.5340 0.03233 0.02076 -0.0427 0.5188 0.9288
2.750 0.5753 0.03235 0.02063 -0.0454 0.5138 0.9331
3.000 0.5836 0.03300 0.02133 -0.0433 0.5071 0.9418
3.250 0.6082 0.03353 0.02185 -0.0438 0.5006 0.9480
3.500 0.6460 0.03365 0.02186 -0.0460 0.4959 0.9534
3.750 0.6667 0.03438 0.02262 -0.0462 0.4899 0.9605
4.000 0.6823 0.03528 0.02359 -0.0458 0.4833 0.9696
4.250 0.7225 0.03553 0.02375 -0.0486 0.4785 0.9750
4.500 0.7589 0.03587 0.02402 -0.0508 0.4742 0.9817
4.750 0.7505 0.03770 0.02606 -0.0479 0.4669 1.0000
5.000 0.7312 0.03838 0.02675 -0.0416 0.4624 1.0000
5.250 0.7556 0.03846 0.02675 -0.0414 0.4590 1.0000
5.500 0.7178 0.04097 0.02939 -0.0348 0.4521 1.0000
5.750 0.7038 0.04345 0.03192 -0.0320 0.4452 1.0000
6.000 0.7338 0.04374 0.03216 -0.0328 0.4419 1.0000
6.250 0.7750 0.04351 0.03183 -0.0345 0.4396 1.0000
6.750 0.7196 0.05194 0.04046 -0.0297 0.4230 1.0000
7.000 0.7590 0.05150 0.03996 -0.0307 0.4213 1.0000
7.500 0.6934 0.06396 0.05261 -0.0300 0.4021 1.0000
8.500 0.6542 0.08210 0.07091 -0.0328 0.3736 1.0000
8.750 0.6753 0.08328 0.07208 -0.0331 0.3707 1.0000
9.000 0.7016 0.08391 0.07269 -0.0333 0.3687 1.0000
9.500 0.6752 0.09398 0.08289 -0.0353 0.3553 1.0000
9.750 0.6978 0.09506 0.08396 -0.0356 0.3527 1.0000
10.250 0.6821 0.10410 0.09312 -0.0379 0.3416 1.0000
10.500 0.6971 0.10602 0.09505 -0.0384 0.3380 1.0000
10.750 0.7196 0.10711 0.09617 -0.0386 0.3355 1.0000
11.000 0.7061 0.11233 0.10145 -0.0401 0.3297 1.0000
11.250 0.7062 0.11598 0.10516 -0.0412 0.3249 1.0000
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Polar data table (+)
Polar graphs
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