Eiffel 371 (Monge) (eiffel371-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: Eiffel 371 (Monge) (eiffel371-il) Reynolds number: 200,000 Max Cl/Cd: 56.23 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-eiffel371-il-200000.txt Download as CSV file: xf-eiffel371-il-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.3914 0.09095 0.08765 -0.0461 1.0000 0.0576
-9.750 -0.3874 0.08897 0.08569 -0.0442 1.0000 0.0586
-9.500 -0.3908 0.08627 0.08304 -0.0435 1.0000 0.0598
-9.250 -0.4032 0.08262 0.07946 -0.0441 1.0000 0.0605
-9.000 -0.4244 0.07845 0.07536 -0.0453 1.0000 0.0611
-8.750 -0.4612 0.07431 0.07125 -0.0456 1.0000 0.0603
-8.500 -0.4976 0.07235 0.06931 -0.0412 1.0000 0.0603
-8.250 -0.5265 0.07031 0.06726 -0.0368 1.0000 0.0604
-8.000 -0.5477 0.06802 0.06494 -0.0331 1.0000 0.0610
-7.750 -0.5368 0.06243 0.05897 -0.0387 0.9911 0.0659
-7.500 -0.5317 0.05582 0.05191 -0.0421 0.9828 0.0693
-7.250 -0.5074 0.05253 0.04867 -0.0435 0.9759 0.0712
-7.000 -0.4795 0.04925 0.04524 -0.0460 0.9707 0.0747
-6.750 -0.4698 0.04578 0.04112 -0.0456 0.9592 0.0826
-6.500 -0.4582 0.03211 0.02610 -0.0419 0.9534 0.0411
-6.250 -0.4321 0.02914 0.02268 -0.0414 0.9450 0.0409
-6.000 -0.3947 0.02568 0.01857 -0.0425 0.9414 0.0396
-5.750 -0.3625 0.02392 0.01663 -0.0430 0.9332 0.0404
-5.500 -0.3209 0.02231 0.01488 -0.0451 0.9283 0.0421
-5.250 -0.2745 0.02100 0.01340 -0.0482 0.9255 0.0451
-5.000 -0.2402 0.01944 0.01180 -0.0490 0.9171 0.0477
-4.750 -0.1975 0.01821 0.01063 -0.0515 0.9118 0.0515
-4.500 -0.1608 0.01720 0.00958 -0.0528 0.9034 0.0573
-4.250 -0.1242 0.01623 0.00865 -0.0541 0.8942 0.0657
-4.000 -0.0957 0.01535 0.00782 -0.0539 0.8805 0.0788
-3.750 -0.0704 0.01430 0.00695 -0.0531 0.8657 0.1141
-3.500 -0.0517 0.01299 0.00626 -0.0514 0.8488 0.2327
-3.250 -0.0450 0.01192 0.00618 -0.0471 0.8302 0.4732
-3.000 -0.0209 0.01204 0.00609 -0.0457 0.8125 0.5446
-2.750 0.0019 0.01193 0.00579 -0.0442 0.7942 0.5764
-2.500 0.0259 0.01139 0.00524 -0.0432 0.7751 0.6083
-2.250 0.0460 0.01086 0.00516 -0.0408 0.7571 0.6475
-2.000 0.0640 0.01155 0.00594 -0.0375 0.7405 0.7613
-1.750 0.0858 0.01182 0.00596 -0.0359 0.7265 0.7797
-1.500 0.1101 0.01203 0.00599 -0.0347 0.7141 0.7942
-1.250 0.1330 0.01212 0.00600 -0.0332 0.7017 0.8095
-1.000 0.1565 0.01214 0.00596 -0.0317 0.6904 0.8266
-0.750 0.1823 0.01216 0.00590 -0.0307 0.6805 0.8423
-0.500 0.2056 0.01220 0.00586 -0.0295 0.6700 0.8510
-0.250 0.2337 0.01228 0.00586 -0.0293 0.6602 0.8555
0.000 0.2601 0.01238 0.00584 -0.0289 0.6510 0.8600
0.250 0.2830 0.01245 0.00584 -0.0278 0.6415 0.8639
0.750 0.3372 0.01265 0.00590 -0.0273 0.6232 0.8701
1.000 0.3645 0.01279 0.00593 -0.0272 0.6150 0.8729
1.250 0.3883 0.01286 0.00598 -0.0263 0.6054 0.8757
1.500 0.4126 0.01297 0.00601 -0.0257 0.5968 0.8783
1.750 0.4362 0.01305 0.00604 -0.0249 0.5876 0.8804
2.000 0.4633 0.01319 0.00614 -0.0247 0.5786 0.8829
2.250 0.4902 0.01332 0.00622 -0.0245 0.5691 0.8862
2.500 0.5138 0.01343 0.00632 -0.0236 0.5585 0.8895
2.750 0.5371 0.01354 0.00636 -0.0227 0.5483 0.8929
3.000 0.5590 0.01360 0.00639 -0.0216 0.5371 0.8954
3.250 0.5829 0.01370 0.00648 -0.0209 0.5251 0.8973
3.500 0.6064 0.01380 0.00654 -0.0202 0.5136 0.8986
3.750 0.6300 0.01390 0.00656 -0.0195 0.5020 0.8997
4.000 0.6505 0.01395 0.00663 -0.0182 0.4888 0.9009
4.250 0.6717 0.01403 0.00671 -0.0172 0.4760 0.9022
4.500 0.6931 0.01413 0.00678 -0.0161 0.4638 0.9027
4.750 0.7140 0.01423 0.00683 -0.0151 0.4512 0.9032
5.000 0.7343 0.01434 0.00689 -0.0139 0.4380 0.9038
5.250 0.7545 0.01445 0.00702 -0.0128 0.4248 0.9043
5.500 0.7750 0.01460 0.00716 -0.0117 0.4123 0.9048
5.750 0.7957 0.01479 0.00731 -0.0107 0.4010 0.9054
6.000 0.8163 0.01502 0.00746 -0.0098 0.3902 0.9059
6.250 0.8367 0.01523 0.00770 -0.0088 0.3789 0.9068
6.500 0.8572 0.01548 0.00794 -0.0079 0.3687 0.9077
6.750 0.8780 0.01580 0.00817 -0.0071 0.3591 0.9085
7.000 0.8981 0.01605 0.00848 -0.0062 0.3490 0.9092
7.250 0.9186 0.01638 0.00880 -0.0054 0.3396 0.9097
7.500 0.9385 0.01671 0.00911 -0.0045 0.3299 0.9103
7.750 0.9576 0.01703 0.00948 -0.0035 0.3202 0.9110
8.000 0.9762 0.01742 0.00982 -0.0025 0.3110 0.9117
8.250 0.9917 0.01769 0.01019 -0.0008 0.3013 0.9127
8.500 1.0084 0.01809 0.01060 0.0006 0.2919 0.9138
8.750 1.0241 0.01851 0.01101 0.0020 0.2821 0.9154
9.000 1.0389 0.01891 0.01152 0.0036 0.2715 0.9177
9.250 1.0538 0.01942 0.01203 0.0051 0.2611 0.9197
9.500 1.0678 0.01998 0.01257 0.0065 0.2503 0.9220
9.750 1.0815 0.02053 0.01321 0.0079 0.2385 0.9249
10.000 1.0962 0.02119 0.01391 0.0089 0.2271 0.9287
10.250 1.1116 0.02194 0.01463 0.0096 0.2179 0.9333
10.500 1.1272 0.02265 0.01541 0.0102 0.2078 0.9397
10.750 1.1455 0.02347 0.01628 0.0100 0.1993 0.9469
11.000 1.1640 0.02432 0.01717 0.0096 0.1919 0.9568
11.250 1.1839 0.02521 0.01815 0.0088 0.1845 0.9704
11.500 1.2019 0.02619 0.01918 0.0084 0.1786 1.0000
11.750 1.2107 0.02712 0.02010 0.0099 0.1741 1.0000
12.000 1.2185 0.02801 0.02112 0.0113 0.1684 1.0000
12.250 1.2241 0.02912 0.02222 0.0127 0.1631 1.0000
12.500 1.2317 0.03022 0.02342 0.0139 0.1584 1.0000
12.750 1.2384 0.03141 0.02471 0.0148 0.1532 1.0000
13.000 1.2435 0.03280 0.02609 0.0158 0.1489 1.0000
13.250 1.2492 0.03423 0.02764 0.0165 0.1439 1.0000
13.500 1.2551 0.03572 0.02924 0.0171 0.1395 1.0000
13.750 1.2547 0.03773 0.03121 0.0178 0.1337 1.0000
14.000 1.2601 0.03947 0.03315 0.0178 0.1285 1.0000
14.250 1.2615 0.04160 0.03536 0.0180 0.1234 1.0000
14.500 1.2618 0.04394 0.03776 0.0180 0.1181 1.0000
14.750 1.2647 0.04619 0.04016 0.0177 0.1122 1.0000
15.000 1.2597 0.04927 0.04324 0.0174 0.1065 1.0000
15.250 1.2638 0.05163 0.04579 0.0168 0.0989 1.0000
15.500 1.2622 0.05462 0.04887 0.0162 0.0898 1.0000
15.750 1.2534 0.05856 0.05278 0.0154 0.0690 1.0000
16.000 1.2356 0.06363 0.05777 0.0143 0.0556 1.0000
16.250 1.2119 0.06963 0.06370 0.0130 0.0429 1.0000
16.500 1.1942 0.07509 0.06921 0.0117 0.0361 1.0000
16.750 1.1810 0.08013 0.07433 0.0102 0.0334 1.0000
17.000 1.1639 0.08593 0.08021 0.0084 0.0308 1.0000
17.250 1.1469 0.09193 0.08632 0.0064 0.0291 1.0000
17.500 1.1343 0.09739 0.09192 0.0045 0.0287 1.0000
17.750 1.1172 0.10372 0.09838 0.0022 0.0278 1.0000
18.000 1.0991 0.11037 0.10516 -0.0004 0.0271 1.0000
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