FX 68-H-120 (fx68h120-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 68-H-120 (fx68h120-il) Reynolds number: 50,000 Max Cl/Cd: 29.22 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx68h120-il-50000-n5.txt Download as CSV file: xf-fx68h120-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 68-H-120
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.4564 0.09695 0.09051 -0.0311 1.0000 0.0432
-10.250 -0.4635 0.09099 0.08464 -0.0343 1.0000 0.0433
-10.000 -0.4736 0.08445 0.07819 -0.0381 1.0000 0.0432
-9.750 -0.4858 0.07742 0.07125 -0.0426 1.0000 0.0427
-9.500 -0.5066 0.06908 0.06295 -0.0493 1.0000 0.0419
-9.250 -0.5317 0.06338 0.05723 -0.0523 1.0000 0.0413
-9.000 -0.5572 0.05940 0.05318 -0.0515 1.0000 0.0409
-8.750 -0.5813 0.05597 0.04961 -0.0490 1.0000 0.0407
-8.500 -0.6023 0.05307 0.04653 -0.0453 1.0000 0.0407
-8.250 -0.6190 0.05021 0.04343 -0.0415 1.0000 0.0408
-8.000 -0.6314 0.04725 0.04013 -0.0377 1.0000 0.0414
-7.750 -0.6377 0.04445 0.03696 -0.0342 1.0000 0.0422
-7.500 -0.6395 0.04171 0.03373 -0.0309 1.0000 0.0437
-7.250 -0.6363 0.03958 0.03141 -0.0280 1.0000 0.0461
-7.000 -0.6292 0.03814 0.02989 -0.0255 1.0000 0.0490
-6.750 -0.6206 0.03618 0.02761 -0.0230 1.0000 0.0523
-6.500 -0.6092 0.03399 0.02495 -0.0205 1.0000 0.0558
-6.250 -0.5975 0.03262 0.02360 -0.0183 1.0000 0.0608
-6.000 -0.5836 0.03122 0.02197 -0.0163 1.0000 0.0699
-5.750 -0.5687 0.03004 0.02070 -0.0143 1.0000 0.0817
-5.500 -0.5543 0.02947 0.02019 -0.0125 1.0000 0.0989
-5.250 -0.5385 0.02886 0.01942 -0.0106 1.0000 0.1229
-5.000 -0.5198 0.02859 0.01887 -0.0095 0.9985 0.1493
-4.750 -0.4935 0.02841 0.01861 -0.0099 0.9940 0.1741
-4.500 -0.4667 0.02799 0.01801 -0.0102 0.9894 0.1950
-4.250 -0.4369 0.02754 0.01742 -0.0110 0.9850 0.2123
-4.000 -0.4070 0.02704 0.01673 -0.0117 0.9805 0.2269
-3.750 -0.3752 0.02659 0.01612 -0.0127 0.9756 0.2411
-3.500 -0.3391 0.02621 0.01555 -0.0146 0.9711 0.2551
-3.250 -0.3061 0.02584 0.01507 -0.0158 0.9649 0.2699
-3.000 -0.2656 0.02553 0.01466 -0.0185 0.9590 0.2873
-2.750 -0.2319 0.02523 0.01429 -0.0198 0.9511 0.3071
-2.500 -0.1922 0.02490 0.01401 -0.0223 0.9438 0.3344
-2.250 -0.1589 0.02451 0.01378 -0.0235 0.9346 0.3698
-2.000 -0.1264 0.02401 0.01362 -0.0246 0.9252 0.4327
-1.750 -0.0895 0.02324 0.01360 -0.0258 0.9171 0.5724
-1.500 0.0473 0.02286 0.01395 -0.0438 0.9161 0.9249
-1.250 0.1326 0.02295 0.01371 -0.0544 0.9083 0.9914
-1.000 0.1798 0.02292 0.01346 -0.0582 0.8971 1.0000
-0.750 0.2121 0.02289 0.01325 -0.0590 0.8839 1.0000
-0.500 0.2419 0.02284 0.01306 -0.0592 0.8700 1.0000
-0.250 0.2697 0.02276 0.01287 -0.0588 0.8552 1.0000
0.000 0.2961 0.02264 0.01265 -0.0581 0.8395 1.0000
0.250 0.3217 0.02248 0.01240 -0.0571 0.8232 1.0000
0.500 0.3471 0.02226 0.01211 -0.0559 0.8063 1.0000
0.750 0.3667 0.02211 0.01190 -0.0538 0.7865 1.0000
1.000 0.3880 0.02186 0.01160 -0.0518 0.7659 1.0000
1.250 0.4075 0.02165 0.01134 -0.0495 0.7429 1.0000
1.500 0.4277 0.02139 0.01103 -0.0473 0.7176 1.0000
1.750 0.4470 0.02120 0.01079 -0.0449 0.6875 1.0000
2.000 0.4683 0.02096 0.01048 -0.0428 0.6541 1.0000
2.250 0.4918 0.02070 0.01006 -0.0409 0.6175 1.0000
2.500 0.5167 0.02049 0.00957 -0.0391 0.5791 1.0000
2.750 0.5395 0.02054 0.00930 -0.0373 0.5411 1.0000
3.000 0.5604 0.02084 0.00930 -0.0355 0.5069 1.0000
3.250 0.5801 0.02129 0.00949 -0.0338 0.4766 1.0000
3.500 0.5997 0.02181 0.00977 -0.0322 0.4509 1.0000
3.750 0.6191 0.02235 0.01016 -0.0307 0.4272 1.0000
4.000 0.6388 0.02291 0.01058 -0.0293 0.4069 1.0000
4.250 0.6588 0.02348 0.01106 -0.0280 0.3881 1.0000
4.500 0.6791 0.02405 0.01154 -0.0267 0.3713 1.0000
4.750 0.6998 0.02464 0.01205 -0.0255 0.3561 1.0000
5.000 0.7210 0.02524 0.01264 -0.0245 0.3425 1.0000
5.250 0.7429 0.02586 0.01323 -0.0235 0.3305 1.0000
5.500 0.7652 0.02649 0.01382 -0.0226 0.3195 1.0000
5.750 0.7875 0.02712 0.01443 -0.0218 0.3092 1.0000
6.000 0.8094 0.02780 0.01519 -0.0209 0.2991 1.0000
6.250 0.8323 0.02850 0.01594 -0.0201 0.2911 1.0000
6.500 0.8550 0.02926 0.01678 -0.0194 0.2836 1.0000
6.750 0.8782 0.03005 0.01761 -0.0187 0.2772 1.0000
7.000 0.8998 0.03089 0.01859 -0.0179 0.2704 1.0000
7.250 0.9229 0.03168 0.01939 -0.0172 0.2649 1.0000
7.500 0.9424 0.03267 0.02067 -0.0162 0.2586 1.0000
7.750 0.9645 0.03355 0.02164 -0.0155 0.2537 1.0000
8.000 0.9860 0.03460 0.02285 -0.0147 0.2497 1.0000
8.250 1.0043 0.03586 0.02440 -0.0137 0.2455 1.0000
8.500 1.0241 0.03704 0.02579 -0.0128 0.2419 1.0000
8.750 1.0461 0.03811 0.02699 -0.0121 0.2387 1.0000
9.000 1.0588 0.03938 0.02856 -0.0105 0.2333 1.0000
9.250 1.0715 0.03933 0.02854 -0.0085 0.2218 1.0000
9.500 1.0764 0.03927 0.02847 -0.0056 0.2084 1.0000
9.750 1.0781 0.03971 0.02906 -0.0027 0.1972 1.0000
10.000 1.0840 0.04068 0.03029 -0.0004 0.1904 1.0000
10.250 1.0840 0.04108 0.03068 0.0027 0.1805 1.0000
10.500 1.0793 0.04221 0.03204 0.0058 0.1718 1.0000
10.750 1.0780 0.04338 0.03335 0.0082 0.1641 1.0000
11.000 1.0745 0.04471 0.03479 0.0103 0.1548 1.0000
11.250 1.0685 0.04674 0.03704 0.0119 0.1432 1.0000
11.500 1.0666 0.04895 0.03949 0.0128 0.1339 1.0000
11.750 1.0648 0.05132 0.04207 0.0135 0.1261 1.0000
12.000 1.0588 0.05452 0.04557 0.0136 0.1140 1.0000
12.250 1.0482 0.05875 0.05016 0.0129 0.1011 1.0000
12.500 1.0305 0.06435 0.05609 0.0113 0.0913 1.0000
13.000 0.9933 0.07575 0.06698 0.0063 0.0459 1.0000
13.500 0.9259 0.09683 0.08908 -0.0030 0.1136 1.0000
13.750 0.9025 0.10533 0.09761 -0.0067 0.1127 1.0000
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Polar data table (+)
Polar graphs
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