Eiffel 371 (Monge) (eiffel371-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: Eiffel 371 (Monge) (eiffel371-il) Reynolds number: 200,000 Max Cl/Cd: 51.98 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-eiffel371-il-200000-n5.txt Download as CSV file: xf-eiffel371-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: Eiffel 371 (Monge)
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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.3809 0.09326 0.08978 -0.0444 1.0000 0.0149
-10.500 -0.4572 0.06904 0.06561 -0.0584 1.0000 0.0137
-10.250 -0.4900 0.06181 0.05832 -0.0628 1.0000 0.0136
-10.000 -0.5145 0.05871 0.05519 -0.0617 1.0000 0.0135
-9.750 -0.5411 0.05489 0.05124 -0.0610 0.9978 0.0135
-9.500 -0.5583 0.04936 0.04538 -0.0622 0.9880 0.0134
-9.250 -0.5669 0.04365 0.03920 -0.0624 0.9785 0.0134
-8.750 -0.5553 0.03625 0.03098 -0.0610 0.9639 0.0141
-8.500 -0.5325 0.03497 0.02960 -0.0614 0.9591 0.0147
-8.250 -0.5174 0.03276 0.02711 -0.0603 0.9514 0.0150
-8.000 -0.4940 0.03032 0.02432 -0.0605 0.9471 0.0155
-7.750 -0.4773 0.02817 0.02180 -0.0589 0.9392 0.0159
-7.500 -0.4519 0.02609 0.01936 -0.0588 0.9340 0.0164
-7.250 -0.4200 0.02417 0.01711 -0.0597 0.9305 0.0170
-7.000 -0.3971 0.02285 0.01556 -0.0586 0.9219 0.0175
-6.750 -0.3656 0.02148 0.01401 -0.0593 0.9162 0.0183
-6.500 -0.3370 0.02066 0.01316 -0.0595 0.9086 0.0197
-6.250 -0.3074 0.01978 0.01219 -0.0598 0.9005 0.0210
-6.000 -0.2779 0.01887 0.01117 -0.0599 0.8920 0.0223
-5.750 -0.2481 0.01804 0.01022 -0.0600 0.8825 0.0234
-5.500 -0.2236 0.01718 0.00935 -0.0594 0.8703 0.0250
-5.250 -0.1957 0.01661 0.00873 -0.0592 0.8571 0.0275
-5.000 -0.1683 0.01605 0.00806 -0.0589 0.8421 0.0302
-4.750 -0.1431 0.01540 0.00737 -0.0582 0.8252 0.0335
-4.500 -0.1161 0.01495 0.00682 -0.0578 0.8067 0.0385
-4.250 -0.0898 0.01447 0.00629 -0.0573 0.7867 0.0466
-4.000 -0.0639 0.01407 0.00585 -0.0567 0.7660 0.0606
-3.750 -0.0398 0.01372 0.00550 -0.0558 0.7457 0.0845
-3.500 -0.0167 0.01341 0.00521 -0.0548 0.7276 0.1150
-3.250 0.0050 0.01307 0.00495 -0.0535 0.7113 0.1626
-3.000 0.0210 0.01242 0.00472 -0.0514 0.6966 0.2702
-2.750 0.0335 0.01189 0.00467 -0.0484 0.6827 0.4192
-2.500 0.0506 0.01186 0.00478 -0.0460 0.6680 0.5059
-2.250 0.0733 0.01203 0.00475 -0.0447 0.6527 0.5413
-2.000 0.0964 0.01213 0.00466 -0.0436 0.6387 0.5585
-1.750 0.1204 0.01213 0.00452 -0.0427 0.6276 0.5707
-1.500 0.1453 0.01211 0.00439 -0.0420 0.6180 0.5803
-1.250 0.1699 0.01202 0.00426 -0.0412 0.6087 0.5928
-1.000 0.1932 0.01186 0.00411 -0.0402 0.6005 0.6093
-0.750 0.2125 0.01166 0.00407 -0.0383 0.5922 0.6274
-0.500 0.2296 0.01178 0.00445 -0.0356 0.5847 0.6481
-0.250 0.2532 0.01214 0.00490 -0.0341 0.5767 0.7387
0.000 0.2783 0.01227 0.00482 -0.0337 0.5689 0.7516
0.250 0.3035 0.01239 0.00482 -0.0333 0.5613 0.7582
0.500 0.3287 0.01253 0.00485 -0.0328 0.5535 0.7629
0.750 0.3538 0.01267 0.00489 -0.0323 0.5461 0.7673
1.000 0.3789 0.01281 0.00495 -0.0317 0.5382 0.7706
1.250 0.4039 0.01294 0.00502 -0.0312 0.5307 0.7740
1.500 0.4288 0.01307 0.00509 -0.0307 0.5227 0.7770
1.750 0.4535 0.01324 0.00516 -0.0301 0.5154 0.7802
2.000 0.4780 0.01334 0.00525 -0.0295 0.5066 0.7831
2.250 0.5019 0.01347 0.00533 -0.0288 0.4974 0.7862
2.500 0.5253 0.01359 0.00541 -0.0280 0.4865 0.7894
2.750 0.5488 0.01373 0.00550 -0.0273 0.4761 0.7922
3.000 0.5718 0.01387 0.00558 -0.0265 0.4652 0.7943
3.250 0.5950 0.01396 0.00567 -0.0258 0.4535 0.7962
3.500 0.6178 0.01408 0.00576 -0.0250 0.4408 0.7980
3.750 0.6400 0.01421 0.00585 -0.0241 0.4269 0.7993
4.000 0.6619 0.01437 0.00596 -0.0232 0.4129 0.8003
4.250 0.6832 0.01455 0.00608 -0.0222 0.3981 0.8011
4.500 0.7040 0.01476 0.00621 -0.0211 0.3837 0.8018
5.000 0.7450 0.01522 0.00657 -0.0190 0.3582 0.8032
5.250 0.7652 0.01547 0.00677 -0.0179 0.3465 0.8040
5.500 0.7846 0.01575 0.00700 -0.0167 0.3357 0.8048
5.750 0.8045 0.01602 0.00724 -0.0156 0.3263 0.8053
6.000 0.8243 0.01629 0.00749 -0.0145 0.3181 0.8060
6.250 0.8428 0.01656 0.00776 -0.0132 0.3100 0.8066
6.500 0.8614 0.01680 0.00801 -0.0119 0.3029 0.8073
6.750 0.8797 0.01706 0.00828 -0.0106 0.2954 0.8078
7.000 0.8971 0.01735 0.00858 -0.0091 0.2884 0.8082
7.250 0.9157 0.01763 0.00891 -0.0079 0.2808 0.8086
7.500 0.9320 0.01799 0.00926 -0.0064 0.2741 0.8090
7.750 0.9508 0.01829 0.00962 -0.0053 0.2664 0.8093
8.000 0.9667 0.01869 0.01002 -0.0038 0.2592 0.8097
8.250 0.9844 0.01904 0.01044 -0.0026 0.2516 0.8100
8.500 0.9993 0.01947 0.01089 -0.0010 0.2435 0.8103
8.750 1.0154 0.01989 0.01135 0.0003 0.2350 0.8105
9.000 1.0285 0.02040 0.01186 0.0020 0.2264 0.8108
9.250 1.0437 0.02087 0.01240 0.0034 0.2176 0.8111
9.500 1.0554 0.02147 0.01300 0.0051 0.2094 0.8112
9.750 1.0696 0.02201 0.01360 0.0065 0.2011 0.8115
10.000 1.0801 0.02271 0.01431 0.0083 0.1926 0.8117
10.250 1.0900 0.02345 0.01506 0.0100 0.1824 0.8122
10.500 1.1000 0.02424 0.01587 0.0116 0.1736 0.8125
10.750 1.1068 0.02520 0.01682 0.0134 0.1644 0.8128
11.000 1.1157 0.02612 0.01777 0.0149 0.1564 0.8129
11.250 1.1220 0.02720 0.01886 0.0165 0.1495 0.8133
11.500 1.1300 0.02825 0.01996 0.0178 0.1434 0.8135
11.750 1.1336 0.02961 0.02131 0.0194 0.1378 0.8137
12.000 1.1431 0.03068 0.02248 0.0202 0.1335 0.8141
12.250 1.1501 0.03196 0.02382 0.0212 0.1291 0.8144
12.500 1.1525 0.03361 0.02552 0.0223 0.1240 0.8145
12.750 1.1595 0.03502 0.02702 0.0229 0.1200 0.8147
13.000 1.1653 0.03659 0.02867 0.0234 0.1141 0.8148
13.250 1.1649 0.03872 0.03081 0.0241 0.1083 0.8149
13.500 1.1717 0.04037 0.03255 0.0243 0.0999 0.8150
13.750 1.1726 0.04260 0.03482 0.0245 0.0935 0.8150
14.000 1.1724 0.04502 0.03723 0.0246 0.0713 0.8151
14.250 1.1522 0.04955 0.04153 0.0247 0.0503 0.8151
14.500 1.1294 0.05462 0.04649 0.0246 0.0245 0.8150
14.750 1.1180 0.05870 0.05060 0.0241 0.0211 0.8150
15.000 1.1088 0.06277 0.05475 0.0234 0.0186 0.8150
15.250 1.1025 0.06660 0.05871 0.0224 0.0173 0.8150
15.500 1.0972 0.07047 0.06272 0.0213 0.0167 0.8150
15.750 1.0856 0.07531 0.06772 0.0199 0.0154 0.8150
16.000 1.0812 0.07931 0.07186 0.0185 0.0154 0.8150
16.250 1.0684 0.08470 0.07740 0.0166 0.0147 0.8150
16.500 1.0563 0.09016 0.08303 0.0146 0.0143 0.8150
16.750 1.0474 0.09526 0.08829 0.0125 0.0143 0.8150
17.000 1.0356 0.10098 0.09416 0.0102 0.0140 0.8150
17.250 1.0244 0.10670 0.10003 0.0078 0.0140 0.8150
17.500 1.0119 0.11279 0.10628 0.0051 0.0138 0.8149
17.750 0.9987 0.11910 0.11273 0.0024 0.0137 0.8150
18.000 0.9848 0.12565 0.11944 -0.0005 0.0136 0.8150
18.250 0.9717 0.13219 0.12611 -0.0034 0.0134 0.8151
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