Falcon (falcon-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: Falcon (falcon-il) Reynolds number: 100,000 Max Cl/Cd: 41.28 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-falcon-il-100000.txt Download as CSV file: xf-falcon-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: Falcon
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.5041 0.11067 0.10549 -0.0140 1.0000 0.1397
-10.250 -0.5033 0.10694 0.10177 -0.0151 1.0000 0.1444
-10.000 -0.5845 0.09826 0.09331 -0.0302 1.0000 0.1499
-9.750 -0.5322 0.09630 0.09131 -0.0217 1.0000 0.1527
-9.500 -0.5174 0.09358 0.08857 -0.0200 1.0000 0.1566
-9.250 -0.5328 0.08853 0.08360 -0.0234 1.0000 0.1627
-8.750 -0.7026 0.05915 0.05340 -0.0309 1.0000 0.0874
-8.500 -0.7083 0.05468 0.04874 -0.0282 1.0000 0.0844
-8.250 -0.7425 0.04824 0.04114 -0.0207 1.0000 0.0773
-8.000 -0.7382 0.04486 0.03744 -0.0177 1.0000 0.0774
-7.750 -0.7257 0.04185 0.03449 -0.0163 1.0000 0.0795
-7.500 -0.7125 0.04004 0.03262 -0.0143 1.0000 0.0818
-7.250 -0.7034 0.03762 0.02990 -0.0114 1.0000 0.0830
-7.000 -0.6931 0.03523 0.02717 -0.0085 1.0000 0.0842
-6.750 -0.6811 0.03316 0.02476 -0.0057 1.0000 0.0861
-6.500 -0.6689 0.03164 0.02281 -0.0027 1.0000 0.0893
-6.250 -0.6533 0.02965 0.02071 -0.0008 1.0000 0.0928
-6.000 -0.6361 0.02838 0.01938 0.0010 1.0000 0.0966
-5.750 -0.6189 0.02721 0.01798 0.0030 1.0000 0.1016
-5.500 -0.6010 0.02588 0.01659 0.0047 1.0000 0.1076
-5.250 -0.5831 0.02500 0.01566 0.0064 1.0000 0.1148
-5.000 -0.5643 0.02390 0.01454 0.0079 1.0000 0.1231
-4.750 -0.5470 0.02329 0.01380 0.0096 1.0000 0.1335
-4.500 -0.5284 0.02232 0.01299 0.0109 1.0000 0.1454
-4.250 -0.5106 0.02154 0.01229 0.0123 1.0000 0.1595
-4.000 -0.4940 0.02084 0.01170 0.0138 1.0000 0.1757
-3.750 -0.4788 0.02022 0.01120 0.0154 1.0000 0.1943
-3.500 -0.4357 0.01907 0.01039 0.0117 0.9917 0.2339
-3.250 -0.3992 0.01723 0.00981 0.0090 0.9809 0.4000
-3.000 -0.3666 0.01619 0.01014 0.0095 0.9698 0.6838
-2.750 -0.3211 0.01632 0.01045 0.0077 0.9582 0.7776
-2.500 -0.2703 0.01659 0.01070 0.0048 0.9472 0.8333
-2.250 -0.2036 0.01699 0.01097 -0.0010 0.9412 0.8729
-2.000 -0.1359 0.01739 0.01121 -0.0072 0.9314 0.8993
-1.750 -0.0482 0.01773 0.01135 -0.0174 0.9265 0.9170
-1.500 0.0349 0.01799 0.01145 -0.0269 0.9146 0.9331
-1.250 0.1133 0.01803 0.01133 -0.0358 0.8985 0.9502
-1.000 0.1714 0.01781 0.01097 -0.0414 0.8755 0.9624
-0.750 0.2217 0.01755 0.01056 -0.0458 0.8502 0.9732
-0.500 0.2696 0.01729 0.01015 -0.0498 0.8243 0.9840
-0.250 0.3172 0.01702 0.00971 -0.0538 0.7996 0.9948
0.000 0.3542 0.01675 0.00929 -0.0560 0.7743 1.0000
0.250 0.3739 0.01663 0.00901 -0.0549 0.7525 1.0000
0.500 0.3940 0.01656 0.00878 -0.0537 0.7324 1.0000
0.750 0.4139 0.01654 0.00864 -0.0526 0.7117 1.0000
1.000 0.4343 0.01654 0.00854 -0.0515 0.6927 1.0000
1.250 0.4550 0.01658 0.00845 -0.0504 0.6745 1.0000
1.500 0.4760 0.01665 0.00841 -0.0493 0.6572 1.0000
1.750 0.4971 0.01674 0.00840 -0.0482 0.6403 1.0000
2.000 0.5183 0.01685 0.00841 -0.0472 0.6240 1.0000
2.250 0.5396 0.01698 0.00846 -0.0461 0.6081 1.0000
2.500 0.5608 0.01713 0.00853 -0.0450 0.5925 1.0000
2.750 0.5818 0.01730 0.00864 -0.0438 0.5774 1.0000
3.000 0.6026 0.01748 0.00876 -0.0426 0.5627 1.0000
3.250 0.6234 0.01768 0.00888 -0.0413 0.5486 1.0000
3.500 0.6445 0.01788 0.00900 -0.0401 0.5349 1.0000
3.750 0.6655 0.01809 0.00915 -0.0388 0.5213 1.0000
4.000 0.6854 0.01832 0.00938 -0.0374 0.5072 1.0000
4.250 0.7054 0.01858 0.00962 -0.0360 0.4934 1.0000
4.500 0.7256 0.01885 0.00988 -0.0346 0.4800 1.0000
4.750 0.7464 0.01913 0.01012 -0.0332 0.4673 1.0000
5.000 0.7678 0.01941 0.01031 -0.0320 0.4549 1.0000
5.250 0.7882 0.01971 0.01060 -0.0306 0.4417 1.0000
5.500 0.8080 0.02006 0.01099 -0.0291 0.4283 1.0000
5.750 0.8283 0.02043 0.01136 -0.0277 0.4152 1.0000
6.000 0.8492 0.02081 0.01172 -0.0264 0.4028 1.0000
6.250 0.8710 0.02120 0.01204 -0.0253 0.3907 1.0000
6.500 0.8916 0.02160 0.01244 -0.0239 0.3778 1.0000
6.750 0.9110 0.02208 0.01298 -0.0225 0.3648 1.0000
7.000 0.9312 0.02262 0.01355 -0.0211 0.3527 1.0000
7.250 0.9528 0.02316 0.01406 -0.0200 0.3416 1.0000
7.500 0.9741 0.02369 0.01456 -0.0188 0.3304 1.0000
7.750 0.9925 0.02434 0.01533 -0.0173 0.3190 1.0000
8.000 1.0135 0.02501 0.01600 -0.0162 0.3091 1.0000
8.250 1.0349 0.02566 0.01667 -0.0151 0.2999 1.0000
8.500 1.0534 0.02654 0.01770 -0.0136 0.2911 1.0000
8.750 1.0768 0.02721 0.01831 -0.0129 0.2833 1.0000
9.000 1.0930 0.02818 0.01951 -0.0112 0.2752 1.0000
9.250 1.1162 0.02889 0.02021 -0.0105 0.2683 1.0000
9.500 1.1317 0.02992 0.02146 -0.0087 0.2609 1.0000
9.750 1.1544 0.03033 0.02179 -0.0079 0.2526 1.0000
10.000 1.1663 0.03101 0.02270 -0.0056 0.2433 1.0000
10.250 1.1855 0.03122 0.02286 -0.0043 0.2336 1.0000
10.500 1.1996 0.03155 0.02328 -0.0023 0.2242 1.0000
10.750 1.2122 0.03212 0.02399 -0.0002 0.2157 1.0000
11.000 1.2309 0.03226 0.02401 0.0011 0.2066 1.0000
11.250 1.2349 0.03285 0.02490 0.0044 0.1975 1.0000
11.500 1.2439 0.03317 0.02528 0.0070 0.1883 1.0000
11.750 1.2491 0.03354 0.02574 0.0100 0.1789 1.0000
12.000 1.2471 0.03424 0.02665 0.0138 0.1696 1.0000
12.250 1.2417 0.03489 0.02735 0.0181 0.1601 1.0000
12.500 1.2323 0.03598 0.02853 0.0219 0.1490 1.0000
12.750 1.2198 0.03781 0.03052 0.0248 0.1355 1.0000
13.000 1.2046 0.04056 0.03336 0.0265 0.1191 1.0000
13.250 1.1874 0.04429 0.03715 0.0272 0.1019 1.0000
13.500 1.1707 0.04854 0.04137 0.0271 0.0902 1.0000
13.750 1.1547 0.05308 0.04584 0.0264 0.0833 1.0000
14.000 1.1417 0.05760 0.05045 0.0255 0.0764 1.0000
14.250 1.1274 0.06231 0.05508 0.0244 0.0727 1.0000
14.500 1.1181 0.06663 0.05954 0.0235 0.0685 1.0000
14.750 1.1077 0.07111 0.06407 0.0223 0.0654 1.0000
15.000 1.0996 0.07512 0.06799 0.0215 0.0626 1.0000
15.250 1.0939 0.07920 0.07224 0.0206 0.0601 1.0000
15.500 1.0900 0.08297 0.07610 0.0199 0.0580 1.0000
15.750 1.0883 0.08640 0.07957 0.0193 0.0560 1.0000
16.000 1.0940 0.08842 0.08150 0.0200 0.0539 1.0000
16.250 1.0967 0.09123 0.08439 0.0202 0.0525 1.0000
16.500 1.0919 0.09556 0.08891 0.0190 0.0518 1.0000
16.750 1.0839 0.10055 0.09409 0.0172 0.0511 1.0000
17.000 1.0732 0.10615 0.09987 0.0150 0.0506 1.0000
17.250 1.0588 0.11259 0.10651 0.0120 0.0503 1.0000
17.500 1.0368 0.12081 0.11495 0.0077 0.0504 1.0000
17.750 1.0033 0.13193 0.12630 0.0014 0.0512 1.0000
18.000 0.9563 0.14699 0.14154 -0.0072 0.0526 1.0000
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Polar data table (+)
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