EPPLER 336 AIRFOIL (e336-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 336 AIRFOIL (e336-il) Reynolds number: 100,000 Max Cl/Cd: 44.78 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e336-il-100000-n5.txt Download as CSV file: xf-e336-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 336 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.4545 0.12577 0.12087 -0.0054 1.0000 0.0447
-11.000 -0.4565 0.12171 0.11686 -0.0085 1.0000 0.0449
-10.750 -0.4587 0.11746 0.11267 -0.0117 1.0000 0.0450
-10.500 -0.4606 0.11301 0.10826 -0.0148 1.0000 0.0451
-10.250 -0.4543 0.10873 0.10404 -0.0150 1.0000 0.0454
-10.000 -0.4461 0.10495 0.10029 -0.0144 1.0000 0.0458
-9.750 -0.4427 0.10109 0.09647 -0.0155 1.0000 0.0462
-9.500 -0.4413 0.09707 0.09250 -0.0170 1.0000 0.0465
-9.000 -0.3721 0.07609 0.07186 -0.0258 1.0000 0.0247
-8.750 -0.3793 0.07139 0.06719 -0.0279 1.0000 0.0242
-8.500 -0.3917 0.06666 0.06246 -0.0296 1.0000 0.0238
-7.500 -0.5144 0.05976 0.05476 -0.0186 1.0000 0.0204
-7.250 -0.5142 0.05702 0.05195 -0.0163 1.0000 0.0201
-7.000 -0.5134 0.05428 0.04912 -0.0137 1.0000 0.0198
-6.750 -0.5077 0.05124 0.04594 -0.0119 0.9896 0.0194
-6.500 -0.4857 0.04674 0.04106 -0.0132 0.9233 0.0189
-6.250 -0.4607 0.04236 0.03615 -0.0140 0.8790 0.0183
-6.000 -0.4423 0.03872 0.03195 -0.0127 0.8428 0.0179
-5.750 -0.4261 0.03557 0.02820 -0.0103 0.8128 0.0174
-5.500 -0.4086 0.03302 0.02512 -0.0080 0.7872 0.0174
-5.250 -0.3890 0.03116 0.02284 -0.0062 0.7638 0.0179
-5.000 -0.3677 0.02943 0.02066 -0.0046 0.7423 0.0189
-4.750 -0.3434 0.02755 0.01821 -0.0031 0.7235 0.0203
-4.500 -0.3187 0.02619 0.01662 -0.0023 0.7063 0.0215
-4.250 -0.2917 0.02484 0.01503 -0.0018 0.6905 0.0223
-4.000 -0.2627 0.02343 0.01336 -0.0015 0.6761 0.0233
-3.750 -0.2341 0.02220 0.01192 -0.0011 0.6625 0.0245
-3.500 -0.2080 0.02119 0.01082 -0.0005 0.6499 0.0262
-3.250 -0.1834 0.02052 0.00999 0.0003 0.6380 0.0301
-3.000 -0.1605 0.01979 0.00925 0.0014 0.6260 0.0343
-2.750 -0.1381 0.01911 0.00847 0.0027 0.6149 0.0399
-2.500 -0.1151 0.01853 0.00781 0.0039 0.6046 0.0533
-2.250 -0.0217 0.01670 0.00927 -0.0055 0.5895 0.8457
-2.000 0.0241 0.01827 0.01049 -0.0064 0.5765 0.9080
-1.750 0.1061 0.01910 0.01087 -0.0152 0.5617 0.9477
-1.500 0.1478 0.01907 0.01056 -0.0179 0.5507 0.9599
-1.000 0.2136 0.01871 0.00978 -0.0203 0.5313 0.9680
-0.750 0.2408 0.01869 0.00956 -0.0204 0.5229 0.9729
-0.500 0.2740 0.01849 0.00920 -0.0218 0.5131 0.9760
-0.250 0.3047 0.01838 0.00894 -0.0227 0.5044 0.9796
0.000 0.3333 0.01834 0.00875 -0.0231 0.4961 0.9834
0.250 0.3644 0.01822 0.00852 -0.0241 0.4881 0.9863
0.500 0.3950 0.01813 0.00831 -0.0249 0.4804 0.9892
0.750 0.4247 0.01808 0.00816 -0.0257 0.4729 0.9923
1.000 0.4543 0.01804 0.00804 -0.0264 0.4654 0.9949
1.250 0.4845 0.01799 0.00788 -0.0272 0.4590 0.9974
1.500 0.5144 0.01797 0.00782 -0.0280 0.4517 0.9999
1.750 0.5376 0.01806 0.00782 -0.0273 0.4464 1.0000
2.000 0.5607 0.01818 0.00794 -0.0267 0.4405 1.0000
2.250 0.5836 0.01831 0.00804 -0.0260 0.4348 1.0000
2.500 0.6066 0.01844 0.00810 -0.0253 0.4303 1.0000
2.750 0.6297 0.01861 0.00829 -0.0247 0.4250 1.0000
3.000 0.6526 0.01877 0.00846 -0.0240 0.4197 1.0000
3.250 0.6755 0.01893 0.00860 -0.0233 0.4154 1.0000
3.500 0.6984 0.01914 0.00881 -0.0227 0.4110 1.0000
3.750 0.7212 0.01935 0.00908 -0.0220 0.4061 1.0000
4.000 0.7439 0.01954 0.00928 -0.0213 0.4015 1.0000
4.250 0.7668 0.01974 0.00947 -0.0206 0.3979 1.0000
4.500 0.7891 0.02001 0.00986 -0.0199 0.3928 1.0000
4.750 0.8114 0.02025 0.01016 -0.0191 0.3881 1.0000
5.000 0.8340 0.02046 0.01038 -0.0183 0.3840 1.0000
5.250 0.8560 0.02074 0.01075 -0.0176 0.3794 1.0000
5.500 0.8776 0.02102 0.01114 -0.0167 0.3744 1.0000
5.750 0.8997 0.02126 0.01143 -0.0159 0.3701 1.0000
6.000 0.9214 0.02153 0.01176 -0.0150 0.3656 1.0000
6.250 0.9421 0.02188 0.01226 -0.0141 0.3603 1.0000
6.500 0.9635 0.02213 0.01255 -0.0131 0.3556 1.0000
6.750 0.9846 0.02243 0.01292 -0.0122 0.3511 1.0000
7.000 1.0042 0.02282 0.01349 -0.0111 0.3453 1.0000
7.250 1.0250 0.02309 0.01380 -0.0100 0.3404 1.0000
7.500 1.0447 0.02347 0.01429 -0.0089 0.3353 1.0000
7.750 1.0631 0.02391 0.01490 -0.0076 0.3292 1.0000
8.000 1.0833 0.02419 0.01521 -0.0065 0.3241 1.0000
8.250 1.1004 0.02468 0.01588 -0.0050 0.3181 1.0000
8.500 1.1177 0.02510 0.01645 -0.0035 0.3116 1.0000
8.750 1.1368 0.02539 0.01677 -0.0022 0.3062 1.0000
9.000 1.1497 0.02597 0.01764 -0.0002 0.2983 1.0000
9.250 1.1669 0.02625 0.01797 0.0014 0.2921 1.0000
9.500 1.1778 0.02686 0.01886 0.0036 0.2842 1.0000
9.750 1.1923 0.02714 0.01923 0.0056 0.2775 1.0000
10.000 1.2008 0.02775 0.02010 0.0082 0.2690 1.0000
10.250 1.2116 0.02811 0.02056 0.0107 0.2617 1.0000
10.500 1.2182 0.02865 0.02129 0.0136 0.2532 1.0000
10.750 1.2235 0.02919 0.02194 0.0167 0.2453 1.0000
11.000 1.2261 0.02972 0.02254 0.0202 0.2375 1.0000
11.250 1.2234 0.03051 0.02345 0.0243 0.2295 1.0000
11.500 1.2159 0.03117 0.02413 0.0291 0.2227 1.0000
11.750 1.2004 0.03212 0.02517 0.0348 0.2167 1.0000
12.000 1.1860 0.03326 0.02637 0.0394 0.2104 1.0000
12.250 1.1727 0.03480 0.02796 0.0429 0.2039 1.0000
12.500 1.1594 0.03678 0.03001 0.0455 0.1969 1.0000
12.750 1.1470 0.03912 0.03242 0.0472 0.1899 1.0000
13.000 1.1341 0.04190 0.03525 0.0482 0.1827 1.0000
13.250 1.1212 0.04503 0.03845 0.0487 0.1756 1.0000
13.500 1.1088 0.04835 0.04179 0.0487 0.1685 1.0000
13.750 1.0953 0.05207 0.04557 0.0484 0.1617 1.0000
14.000 1.0834 0.05569 0.04921 0.0480 0.1548 1.0000
14.250 1.0703 0.05972 0.05330 0.0473 0.1482 1.0000
14.500 1.0602 0.06338 0.05698 0.0466 0.1415 1.0000
14.750 1.0484 0.06753 0.06120 0.0456 0.1351 1.0000
15.000 1.0400 0.07128 0.06495 0.0446 0.1285 1.0000
15.250 1.0304 0.07545 0.06919 0.0434 0.1224 1.0000
15.500 1.0231 0.07931 0.07307 0.0422 0.1162 1.0000
15.750 1.0155 0.08341 0.07722 0.0409 0.1104 1.0000
16.000 1.0086 0.08748 0.08133 0.0395 0.1047 1.0000
16.250 1.0035 0.09131 0.08518 0.0382 0.0994 1.0000
16.500 0.9956 0.09581 0.08977 0.0365 0.0941 1.0000
16.750 0.9933 0.09925 0.09317 0.0353 0.0891 1.0000
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