EPPLER 297 AIRFOIL (e297-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 297 AIRFOIL (e297-il) Reynolds number: 200,000 Max Cl/Cd: 39.58 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e297-il-200000-n5.txt Download as CSV file: xf-e297-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 297 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.7035 0.10102 0.09765 -0.0079 1.0000 0.0060
-12.500 -0.7336 0.08659 0.08314 -0.0164 1.0000 0.0058
-12.250 -0.7545 0.07657 0.07300 -0.0236 1.0000 0.0057
-12.000 -0.7757 0.06843 0.06470 -0.0294 1.0000 0.0056
-11.750 -0.7968 0.06178 0.05786 -0.0333 1.0000 0.0056
-11.500 -0.8140 0.05667 0.05256 -0.0354 1.0000 0.0055
-11.250 -0.8308 0.05218 0.04785 -0.0361 1.0000 0.0055
-11.000 -0.8481 0.04796 0.04337 -0.0357 1.0000 0.0055
-10.750 -0.8600 0.04457 0.03972 -0.0344 1.0000 0.0055
-10.500 -0.8691 0.04153 0.03641 -0.0325 1.0000 0.0055
-10.250 -0.8746 0.03884 0.03344 -0.0301 1.0000 0.0055
-10.000 -0.8773 0.03625 0.03055 -0.0274 1.0000 0.0056
-9.750 -0.8746 0.03391 0.02792 -0.0249 1.0000 0.0057
-9.500 -0.8670 0.03153 0.02522 -0.0229 1.0000 0.0059
-9.250 -0.8554 0.02953 0.02297 -0.0213 1.0000 0.0060
-9.000 -0.8420 0.02768 0.02083 -0.0197 1.0000 0.0062
-8.750 -0.8271 0.02608 0.01902 -0.0182 1.0000 0.0065
-8.500 -0.8141 0.02435 0.01713 -0.0165 1.0000 0.0069
-8.250 -0.8012 0.02294 0.01560 -0.0148 1.0000 0.0074
-8.000 -0.7866 0.02198 0.01457 -0.0131 1.0000 0.0084
-7.750 -0.7663 0.02113 0.01363 -0.0126 0.9930 0.0098
-7.500 -0.7386 0.02005 0.01241 -0.0135 0.9809 0.0126
-7.250 -0.7117 0.01893 0.01121 -0.0143 0.9708 0.0166
-7.000 -0.6847 0.01798 0.01020 -0.0149 0.9620 0.0232
-6.750 -0.6568 0.01719 0.00928 -0.0156 0.9547 0.0311
-6.500 -0.6316 0.01648 0.00853 -0.0157 0.9468 0.0413
-6.250 -0.6066 0.01574 0.00783 -0.0157 0.9403 0.0577
-6.000 -0.5834 0.01516 0.00726 -0.0153 0.9329 0.0777
-5.750 -0.5596 0.01456 0.00675 -0.0150 0.9272 0.1063
-5.500 -0.5383 0.01395 0.00630 -0.0143 0.9204 0.1467
-5.250 -0.5174 0.01330 0.00587 -0.0135 0.9148 0.2001
-5.000 -0.4972 0.01268 0.00549 -0.0126 0.9090 0.2601
-4.750 -0.4772 0.01209 0.00510 -0.0116 0.9033 0.3256
-4.500 -0.4569 0.01154 0.00480 -0.0104 0.8987 0.3934
-4.250 -0.4363 0.01107 0.00457 -0.0093 0.8931 0.4596
-4.000 -0.4149 0.01068 0.00441 -0.0082 0.8885 0.5230
-3.750 -0.3921 0.01042 0.00433 -0.0071 0.8844 0.5791
-3.500 -0.3679 0.01029 0.00433 -0.0063 0.8796 0.6241
-3.250 -0.3427 0.01027 0.00433 -0.0055 0.8754 0.6576
-3.000 -0.3169 0.01029 0.00435 -0.0048 0.8719 0.6838
-2.750 -0.2909 0.01034 0.00437 -0.0044 0.8670 0.7051
-2.500 -0.2648 0.01039 0.00438 -0.0039 0.8626 0.7227
-2.250 -0.2384 0.01045 0.00437 -0.0034 0.8590 0.7373
-2.000 -0.2121 0.01050 0.00439 -0.0030 0.8541 0.7500
-1.750 -0.1857 0.01055 0.00439 -0.0026 0.8495 0.7610
-1.500 -0.1591 0.01060 0.00441 -0.0021 0.8456 0.7701
-1.250 -0.1327 0.01064 0.00441 -0.0018 0.8404 0.7791
-1.000 -0.1062 0.01067 0.00442 -0.0014 0.8353 0.7876
-0.750 -0.0795 0.01069 0.00441 -0.0010 0.8312 0.7943
-0.500 -0.0531 0.01071 0.00443 -0.0008 0.8251 0.8018
-0.250 -0.0265 0.01072 0.00442 -0.0004 0.8198 0.8076
0.000 0.0000 0.01072 0.00443 0.0000 0.8141 0.8141
0.250 0.0265 0.01072 0.00442 0.0004 0.8076 0.8198
0.500 0.0531 0.01071 0.00443 0.0008 0.8018 0.8251
0.750 0.0795 0.01069 0.00441 0.0010 0.7943 0.8312
1.000 0.1063 0.01067 0.00441 0.0014 0.7876 0.8354
1.250 0.1327 0.01064 0.00441 0.0018 0.7792 0.8404
1.500 0.1591 0.01060 0.00441 0.0021 0.7701 0.8456
1.750 0.1857 0.01055 0.00439 0.0026 0.7610 0.8495
2.000 0.2121 0.01050 0.00438 0.0030 0.7500 0.8541
2.250 0.2385 0.01045 0.00437 0.0034 0.7373 0.8590
2.500 0.2648 0.01039 0.00438 0.0039 0.7228 0.8627
2.750 0.2909 0.01034 0.00437 0.0044 0.7051 0.8670
3.000 0.3170 0.01029 0.00435 0.0048 0.6838 0.8719
3.250 0.3428 0.01027 0.00433 0.0055 0.6575 0.8754
3.500 0.3680 0.01029 0.00433 0.0062 0.6239 0.8796
3.750 0.3922 0.01042 0.00433 0.0071 0.5787 0.8845
4.000 0.4151 0.01067 0.00441 0.0081 0.5232 0.8886
4.250 0.4365 0.01107 0.00457 0.0093 0.4597 0.8932
4.500 0.4571 0.01155 0.00480 0.0104 0.3928 0.8987
4.750 0.4774 0.01209 0.00510 0.0115 0.3249 0.9034
5.000 0.4975 0.01268 0.00549 0.0125 0.2596 0.9089
5.250 0.5178 0.01331 0.00587 0.0134 0.1996 0.9148
5.500 0.5388 0.01395 0.00630 0.0142 0.1463 0.9204
5.750 0.5601 0.01457 0.00675 0.0149 0.1058 0.9272
6.000 0.5839 0.01516 0.00727 0.0152 0.0776 0.9329
6.250 0.6072 0.01575 0.00784 0.0156 0.0575 0.9403
6.500 0.6323 0.01649 0.00853 0.0155 0.0413 0.9468
6.750 0.6574 0.01720 0.00928 0.0155 0.0309 0.9547
7.000 0.6854 0.01798 0.01020 0.0148 0.0230 0.9621
7.250 0.7125 0.01893 0.01121 0.0141 0.0166 0.9709
7.500 0.7395 0.02003 0.01240 0.0134 0.0128 0.9812
8.000 0.7875 0.02193 0.01450 0.0130 0.0082 1.0000
8.250 0.8019 0.02296 0.01562 0.0146 0.0073 1.0000
8.500 0.8131 0.02469 0.01749 0.0166 0.0067 1.0000
8.750 0.8283 0.02612 0.01906 0.0180 0.0065 1.0000
9.000 0.8433 0.02777 0.02093 0.0195 0.0062 1.0000
9.250 0.8568 0.02963 0.02309 0.0210 0.0059 1.0000
9.500 0.8684 0.03164 0.02535 0.0226 0.0058 1.0000
9.750 0.8763 0.03397 0.02799 0.0246 0.0057 1.0000
10.000 0.8787 0.03641 0.03073 0.0271 0.0056 1.0000
10.250 0.8774 0.03879 0.03338 0.0297 0.0056 1.0000
10.500 0.8709 0.04161 0.03650 0.0321 0.0055 1.0000
10.750 0.8598 0.04491 0.04009 0.0342 0.0055 1.0000
11.000 0.8484 0.04824 0.04367 0.0354 0.0055 1.0000
11.250 0.8323 0.05232 0.04799 0.0357 0.0055 1.0000
11.500 0.8145 0.05696 0.05287 0.0349 0.0055 1.0000
11.750 0.7984 0.06193 0.05801 0.0329 0.0056 1.0000
12.000 0.7770 0.06865 0.06492 0.0289 0.0057 1.0000
12.250 0.7571 0.07654 0.07297 0.0233 0.0057 1.0000
12.500 0.7339 0.08726 0.08383 0.0156 0.0058 1.0000
12.750 0.7061 0.10102 0.09765 0.0075 0.0060 1.0000
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Polar data table (+)
Polar graphs
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