E169 (14.4%) (e169-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: E169 (14.4%) (e169-il) Reynolds number: 500,000 Max Cl/Cd: 77.74 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e169-il-500000.txt Download as CSV file: xf-e169-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: E169 (14.4%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.750 -1.0971 0.08590 0.08146 -0.0089 1.0000 0.0146
-16.500 -1.1028 0.08157 0.07708 -0.0108 1.0000 0.0149
-16.250 -1.1083 0.07726 0.07270 -0.0127 1.0000 0.0153
-16.000 -1.1139 0.07297 0.06835 -0.0145 1.0000 0.0156
-15.750 -1.1183 0.06895 0.06426 -0.0162 1.0000 0.0159
-15.500 -1.1227 0.06500 0.06023 -0.0178 1.0000 0.0164
-15.250 -1.1280 0.06111 0.05626 -0.0193 1.0000 0.0167
-15.000 -1.1323 0.05747 0.05252 -0.0205 1.0000 0.0170
-14.750 -1.1360 0.05392 0.04887 -0.0218 1.0000 0.0175
-14.500 -1.1376 0.05067 0.04551 -0.0228 1.0000 0.0178
-14.250 -1.1480 0.04654 0.04130 -0.0240 1.0000 0.0182
-14.000 -1.1572 0.04259 0.03726 -0.0252 1.0000 0.0185
-13.750 -1.1639 0.03897 0.03357 -0.0262 1.0000 0.0191
-13.500 -1.1666 0.03587 0.03040 -0.0270 1.0000 0.0196
-13.250 -1.1665 0.03319 0.02764 -0.0275 1.0000 0.0202
-13.000 -1.1647 0.03082 0.02519 -0.0277 1.0000 0.0211
-12.750 -1.1607 0.02884 0.02311 -0.0275 1.0000 0.0218
-12.500 -1.1570 0.02703 0.02119 -0.0270 1.0000 0.0225
-12.250 -1.1642 0.02478 0.01886 -0.0254 1.0000 0.0235
-12.000 -1.1626 0.02343 0.01746 -0.0233 1.0000 0.0247
-11.750 -1.1575 0.02243 0.01640 -0.0209 1.0000 0.0259
-11.500 -1.1494 0.02165 0.01556 -0.0185 1.0000 0.0273
-11.250 -1.1417 0.02067 0.01451 -0.0160 1.0000 0.0289
-11.000 -1.1306 0.01971 0.01354 -0.0141 1.0000 0.0313
-10.750 -1.1145 0.01902 0.01279 -0.0126 1.0000 0.0339
-10.500 -1.1007 0.01810 0.01186 -0.0109 1.0000 0.0382
-10.250 -1.0831 0.01740 0.01114 -0.0096 1.0000 0.0433
-10.000 -1.0663 0.01662 0.01039 -0.0082 1.0000 0.0512
-9.750 -1.0486 0.01586 0.00968 -0.0069 1.0000 0.0613
-9.500 -1.0298 0.01517 0.00904 -0.0057 1.0000 0.0731
-9.250 -1.0105 0.01451 0.00844 -0.0045 1.0000 0.0864
-9.000 -0.9910 0.01385 0.00786 -0.0033 1.0000 0.1021
-8.750 -0.9709 0.01325 0.00734 -0.0023 1.0000 0.1194
-8.500 -0.9498 0.01273 0.00689 -0.0012 1.0000 0.1373
-8.250 -0.9284 0.01225 0.00648 -0.0002 1.0000 0.1549
-8.000 -0.9067 0.01181 0.00611 0.0007 1.0000 0.1727
-7.750 -0.8844 0.01143 0.00579 0.0017 1.0000 0.1892
-7.500 -0.8617 0.01109 0.00550 0.0026 1.0000 0.2040
-7.250 -0.8387 0.01079 0.00523 0.0035 1.0000 0.2179
-7.000 -0.8157 0.01050 0.00498 0.0043 1.0000 0.2326
-6.750 -0.7927 0.01023 0.00476 0.0052 1.0000 0.2485
-6.500 -0.7696 0.00999 0.00456 0.0061 1.0000 0.2623
-6.250 -0.7465 0.00978 0.00438 0.0070 1.0000 0.2739
-6.000 -0.7097 0.00958 0.00419 0.0051 0.9949 0.2872
-5.750 -0.6685 0.00938 0.00402 0.0022 0.9837 0.3009
-5.500 -0.6286 0.00921 0.00385 -0.0002 0.9646 0.3144
-5.250 -0.5828 0.00903 0.00366 -0.0039 0.9343 0.3281
-5.000 -0.5440 0.00891 0.00348 -0.0060 0.8908 0.3399
-4.750 -0.5177 0.00891 0.00334 -0.0053 0.8480 0.3495
-4.500 -0.4919 0.00895 0.00321 -0.0046 0.8135 0.3592
-4.250 -0.4663 0.00891 0.00310 -0.0040 0.7845 0.3682
-4.000 -0.4397 0.00890 0.00298 -0.0035 0.7589 0.3768
-3.750 -0.4134 0.00888 0.00287 -0.0031 0.7358 0.3852
-3.500 -0.3863 0.00886 0.00277 -0.0027 0.7140 0.3934
-3.250 -0.3593 0.00883 0.00268 -0.0024 0.6941 0.4016
-3.000 -0.3321 0.00881 0.00258 -0.0021 0.6755 0.4096
-2.750 -0.3048 0.00880 0.00251 -0.0019 0.6580 0.4179
-2.500 -0.2774 0.00877 0.00243 -0.0016 0.6417 0.4255
-2.250 -0.2498 0.00877 0.00236 -0.0014 0.6259 0.4340
-2.000 -0.2223 0.00874 0.00230 -0.0012 0.6109 0.4418
-1.750 -0.1945 0.00873 0.00225 -0.0011 0.5966 0.4505
-1.500 -0.1669 0.00870 0.00220 -0.0009 0.5830 0.4585
-1.250 -0.1389 0.00871 0.00216 -0.0008 0.5702 0.4675
-1.000 -0.1114 0.00868 0.00213 -0.0006 0.5580 0.4760
-0.750 -0.0835 0.00870 0.00210 -0.0004 0.5463 0.4850
-0.500 -0.0557 0.00867 0.00209 -0.0003 0.5348 0.4943
-0.250 -0.0278 0.00866 0.00207 -0.0001 0.5241 0.5037
0.000 0.0000 0.00869 0.00207 0.0000 0.5140 0.5139
0.250 0.0278 0.00866 0.00207 0.0001 0.5037 0.5241
0.500 0.0557 0.00867 0.00209 0.0003 0.4943 0.5348
0.750 0.0835 0.00870 0.00210 0.0004 0.4850 0.5463
1.000 0.1114 0.00868 0.00213 0.0006 0.4760 0.5580
1.250 0.1389 0.00871 0.00216 0.0008 0.4675 0.5702
1.500 0.1668 0.00870 0.00220 0.0009 0.4586 0.5830
1.750 0.1945 0.00873 0.00225 0.0011 0.4505 0.5966
2.000 0.2223 0.00874 0.00230 0.0012 0.4418 0.6109
2.250 0.2498 0.00877 0.00236 0.0014 0.4340 0.6259
2.500 0.2774 0.00877 0.00243 0.0016 0.4256 0.6417
2.750 0.3048 0.00880 0.00251 0.0019 0.4179 0.6581
3.000 0.3321 0.00881 0.00258 0.0021 0.4096 0.6755
3.250 0.3593 0.00883 0.00268 0.0024 0.4016 0.6941
3.500 0.3863 0.00886 0.00277 0.0027 0.3934 0.7140
4.000 0.4397 0.00890 0.00298 0.0035 0.3768 0.7588
4.250 0.4663 0.00891 0.00310 0.0040 0.3681 0.7845
4.500 0.4919 0.00895 0.00321 0.0046 0.3592 0.8135
4.750 0.5176 0.00891 0.00334 0.0054 0.3495 0.8481
5.000 0.5440 0.00891 0.00348 0.0060 0.3399 0.8909
5.250 0.5827 0.00902 0.00366 0.0039 0.3280 0.9342
5.500 0.6286 0.00921 0.00385 0.0002 0.3145 0.9645
5.750 0.6685 0.00938 0.00402 -0.0022 0.3009 0.9836
6.000 0.7095 0.00958 0.00420 -0.0050 0.2873 0.9948
6.250 0.7466 0.00978 0.00438 -0.0071 0.2739 1.0000
6.500 0.7698 0.00999 0.00456 -0.0062 0.2623 1.0000
6.750 0.7928 0.01023 0.00476 -0.0053 0.2485 1.0000
7.000 0.8158 0.01050 0.00499 -0.0044 0.2326 1.0000
7.250 0.8388 0.01079 0.00523 -0.0035 0.2178 1.0000
7.500 0.8618 0.01109 0.00550 -0.0026 0.2040 1.0000
7.750 0.8845 0.01143 0.00579 -0.0017 0.1891 1.0000
8.000 0.9068 0.01181 0.00611 -0.0008 0.1725 1.0000
8.250 0.9285 0.01225 0.00648 0.0002 0.1550 1.0000
8.500 0.9498 0.01273 0.00689 0.0012 0.1374 1.0000
8.750 0.9709 0.01325 0.00734 0.0023 0.1194 1.0000
9.000 0.9911 0.01385 0.00785 0.0033 0.1022 1.0000
9.250 1.0105 0.01450 0.00843 0.0045 0.0866 1.0000
9.500 1.0297 0.01517 0.00904 0.0057 0.0730 1.0000
9.750 1.0485 0.01586 0.00968 0.0069 0.0613 1.0000
10.000 1.0661 0.01661 0.01039 0.0082 0.0512 1.0000
10.250 1.0831 0.01740 0.01114 0.0096 0.0434 1.0000
10.500 1.1006 0.01809 0.01185 0.0109 0.0382 1.0000
10.750 1.1143 0.01901 0.01278 0.0127 0.0339 1.0000
11.000 1.1305 0.01970 0.01353 0.0141 0.0314 1.0000
11.250 1.1417 0.02065 0.01449 0.0161 0.0290 1.0000
11.500 1.1493 0.02164 0.01555 0.0185 0.0272 1.0000
11.750 1.1576 0.02241 0.01638 0.0209 0.0259 1.0000
12.000 1.1629 0.02339 0.01743 0.0233 0.0247 1.0000
12.250 1.1643 0.02476 0.01884 0.0254 0.0236 1.0000
12.500 1.1573 0.02700 0.02116 0.0270 0.0225 1.0000
12.750 1.1613 0.02877 0.02304 0.0276 0.0218 1.0000
13.000 1.1642 0.03086 0.02523 0.0277 0.0211 1.0000
13.250 1.1659 0.03325 0.02770 0.0275 0.0204 1.0000
13.500 1.1667 0.03585 0.03039 0.0270 0.0197 1.0000
13.750 1.1655 0.03879 0.03340 0.0262 0.0191 1.0000
14.000 1.1582 0.04249 0.03717 0.0252 0.0185 1.0000
14.250 1.1470 0.04667 0.04143 0.0239 0.0181 1.0000
14.500 1.1400 0.05044 0.04528 0.0228 0.0178 1.0000
14.750 1.1380 0.05374 0.04870 0.0217 0.0173 1.0000
15.000 1.1335 0.05736 0.05241 0.0205 0.0170 1.0000
15.250 1.1291 0.06104 0.05619 0.0192 0.0165 1.0000
15.500 1.1244 0.06489 0.06011 0.0177 0.0161 1.0000
15.750 1.1193 0.06889 0.06419 0.0161 0.0158 1.0000
16.000 1.1142 0.07294 0.06832 0.0145 0.0156 1.0000
16.250 1.1095 0.07716 0.07260 0.0126 0.0152 1.0000
16.500 1.1040 0.08148 0.07698 0.0107 0.0149 1.0000
16.750 1.0996 0.08563 0.08120 0.0089 0.0147 1.0000
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Polar data table (+)
Polar graphs
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