EPPLER 1233 AIRFOIL (e1233-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 1233 AIRFOIL (e1233-il) Reynolds number: 100,000 Max Cl/Cd: 34.05 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e1233-il-100000.txt Download as CSV file: xf-e1233-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3749 0.10606 0.10224 -0.0476 0.9911 0.1424
-9.000 -0.3202 0.10187 0.09802 -0.0456 0.9877 0.1448
-8.750 -0.5012 0.06679 0.06213 -0.0712 0.9623 0.0711
-8.500 -0.4949 0.06080 0.05584 -0.0741 0.9499 0.0676
-8.250 -0.5149 0.05160 0.04558 -0.0754 0.9352 0.0627
-8.000 -0.5038 0.04699 0.04023 -0.0759 0.9224 0.0618
-7.750 -0.4826 0.04333 0.03615 -0.0766 0.9112 0.0622
-7.500 -0.4401 0.04089 0.03376 -0.0801 0.9053 0.0648
-7.250 -0.4156 0.03862 0.03113 -0.0804 0.8930 0.0678
-7.000 -0.3737 0.03543 0.02747 -0.0834 0.8881 0.0714
-6.750 -0.3452 0.03375 0.02572 -0.0836 0.8759 0.0746
-6.500 -0.2977 0.03136 0.02310 -0.0869 0.8716 0.0818
-6.250 -0.2671 0.02991 0.02143 -0.0871 0.8597 0.0897
-6.000 -0.2163 0.02781 0.01944 -0.0910 0.8550 0.1035
-5.750 -0.1801 0.02641 0.01813 -0.0924 0.8444 0.1201
-5.500 -0.1299 0.02470 0.01648 -0.0964 0.8374 0.1470
-5.250 -0.0941 0.02361 0.01544 -0.0978 0.8256 0.1732
-5.000 -0.0457 0.02215 0.01414 -0.1015 0.8171 0.2090
-4.750 -0.0192 0.02123 0.01345 -0.1013 0.8027 0.2438
-4.500 0.0082 0.02005 0.01271 -0.1014 0.7899 0.3075
-4.250 0.0299 0.01873 0.01264 -0.0999 0.7788 0.5034
-4.000 0.0497 0.01962 0.01372 -0.0960 0.7641 0.6103
-3.750 0.0770 0.02066 0.01460 -0.0937 0.7509 0.6534
-3.500 0.1139 0.02167 0.01534 -0.0928 0.7399 0.6824
-3.250 0.1320 0.02254 0.01610 -0.0892 0.7259 0.7017
-3.000 0.1570 0.02331 0.01671 -0.0867 0.7138 0.7201
-2.750 0.1876 0.02395 0.01712 -0.0853 0.7030 0.7380
-2.500 0.2063 0.02455 0.01763 -0.0820 0.6906 0.7529
-2.250 0.2431 0.02516 0.01802 -0.0813 0.6807 0.7673
-2.000 0.2646 0.02554 0.01831 -0.0787 0.6690 0.7823
-1.750 0.2967 0.02593 0.01853 -0.0778 0.6588 0.7990
-1.500 0.3287 0.02620 0.01865 -0.0772 0.6484 0.8158
-1.250 0.3572 0.02638 0.01869 -0.0765 0.6388 0.8315
-1.000 0.3845 0.02641 0.01857 -0.0760 0.6293 0.8450
-0.750 0.4309 0.02642 0.01843 -0.0789 0.6193 0.8539
-0.500 0.4429 0.02632 0.01824 -0.0763 0.6111 0.8651
-0.250 0.4914 0.02628 0.01803 -0.0802 0.6023 0.8719
0.000 0.4931 0.02624 0.01797 -0.0758 0.5946 0.8818
0.250 0.5520 0.02612 0.01757 -0.0818 0.5866 0.8870
0.500 0.5364 0.02617 0.01774 -0.0743 0.5795 0.8971
0.750 0.5897 0.02607 0.01745 -0.0794 0.5714 0.9013
1.000 0.6130 0.02615 0.01746 -0.0791 0.5647 0.9078
1.250 0.6196 0.02620 0.01754 -0.0758 0.5580 0.9147
1.500 0.6652 0.02612 0.01727 -0.0795 0.5513 0.9187
1.750 0.6714 0.02631 0.01749 -0.0762 0.5452 0.9257
2.000 0.6919 0.02640 0.01759 -0.0755 0.5384 0.9308
2.250 0.7322 0.02642 0.01745 -0.0784 0.5328 0.9349
2.500 0.7393 0.02669 0.01775 -0.0752 0.5277 0.9417
2.750 0.7634 0.02695 0.01806 -0.0754 0.5209 0.9461
3.000 0.7986 0.02703 0.01804 -0.0773 0.5155 0.9505
3.250 0.8194 0.02727 0.01821 -0.0767 0.5107 0.9563
3.500 0.8404 0.02775 0.01882 -0.0766 0.5040 0.9610
3.750 0.8684 0.02800 0.01904 -0.0773 0.4989 0.9659
4.000 0.9066 0.02816 0.01907 -0.0798 0.4948 0.9701
4.250 0.9246 0.02888 0.01994 -0.0794 0.4887 0.9757
4.500 0.9424 0.02937 0.02049 -0.0785 0.4832 0.9814
4.750 0.9847 0.02956 0.02060 -0.0819 0.4785 0.9849
5.000 1.0225 0.03003 0.02101 -0.0847 0.4745 0.9894
5.250 1.0300 0.03119 0.02241 -0.0828 0.4688 0.9969
5.500 1.0438 0.03182 0.02310 -0.0814 0.4642 1.0000
5.750 1.0557 0.03210 0.02335 -0.0793 0.4607 1.0000
6.000 1.0836 0.03230 0.02342 -0.0797 0.4575 1.0000
6.250 1.0315 0.03365 0.02504 -0.0675 0.4541 1.0000
6.500 0.9671 0.03523 0.02684 -0.0541 0.4504 1.0000
6.750 0.9602 0.03661 0.02829 -0.0504 0.4461 1.0000
7.000 0.9975 0.03687 0.02850 -0.0524 0.4428 1.0000
7.250 1.0513 0.03668 0.02819 -0.0566 0.4398 1.0000
7.500 0.7774 0.05636 0.04855 -0.0350 0.4228 1.0000
7.750 0.8476 0.05267 0.04479 -0.0364 0.4229 1.0000
8.000 0.9332 0.04860 0.04063 -0.0397 0.4229 1.0000
8.250 1.0167 0.04584 0.03776 -0.0445 0.4220 1.0000
9.500 0.5187 0.11750 0.11024 -0.0488 0.4290 1.0000
9.750 0.5414 0.11970 0.11244 -0.0496 0.4250 1.0000
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Polar data table (+)
Polar graphs
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