FX 60-177 AIRFOIL (fx60177-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 60-177 AIRFOIL (fx60177-il) Reynolds number: 100,000 Max Cl/Cd: 40.42 at α=9° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx60177-il-100000.txt Download as CSV file: xf-fx60177-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: FX 60-177 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-12.000 -0.4648 0.10214 0.09781 -0.0525 1.0001 0.0527
-11.750 -0.6049 0.08129 0.07643 -0.0629 1.0001 0.0454
-11.500 -0.6186 0.07717 0.07224 -0.0619 1.0001 0.0447
-11.250 -0.7210 0.07789 0.07246 -0.0621 1.0001 0.0444
-11.000 -0.7414 0.07481 0.06932 -0.0595 1.0001 0.0440
-10.750 -0.7650 0.07215 0.06658 -0.0562 1.0001 0.0436
-10.500 -0.7904 0.06991 0.06425 -0.0522 1.0001 0.0433
-10.250 -0.8170 0.06796 0.06222 -0.0475 1.0001 0.0430
-10.000 -0.8373 0.06532 0.05943 -0.0440 1.0001 0.0425
-9.750 -0.8532 0.06235 0.05626 -0.0407 1.0001 0.0420
-9.500 -0.8652 0.05917 0.05281 -0.0376 1.0001 0.0413
-9.250 -0.8731 0.05584 0.04916 -0.0347 1.0001 0.0407
-9.000 -0.8756 0.05253 0.04546 -0.0322 1.0001 0.0402
-8.750 -0.8723 0.04946 0.04202 -0.0301 1.0001 0.0400
-8.500 -0.8640 0.04683 0.03906 -0.0283 1.0001 0.0403
-8.250 -0.8526 0.04464 0.03658 -0.0267 1.0001 0.0414
-8.000 -0.8392 0.04267 0.03427 -0.0252 1.0001 0.0432
-7.750 -0.8241 0.04114 0.03227 -0.0238 1.0001 0.0451
-7.500 -0.8073 0.03872 0.02996 -0.0225 1.0001 0.0480
-7.250 -0.7898 0.03734 0.02847 -0.0211 1.0001 0.0519
-7.000 -0.7716 0.03567 0.02664 -0.0194 1.0001 0.0566
-6.750 -0.7549 0.03472 0.02574 -0.0185 1.0001 0.0645
-6.500 -0.7380 0.03356 0.02468 -0.0176 1.0001 0.0735
-6.250 -0.7199 0.03251 0.02358 -0.0162 1.0001 0.0817
-6.000 -0.7017 0.03159 0.02274 -0.0151 1.0001 0.0909
-5.750 -0.6836 0.03044 0.02174 -0.0140 1.0001 0.1016
-5.500 -0.6632 0.02936 0.02077 -0.0138 1.0001 0.1220
-5.250 -0.6361 0.02708 0.01932 -0.0163 1.0001 0.1980
-5.000 -0.6100 0.02538 0.02009 -0.0174 1.0001 0.5421
-4.750 -0.5974 0.02657 0.02136 -0.0134 1.0001 0.6015
-4.500 -0.5843 0.02792 0.02262 -0.0096 1.0001 0.6338
-4.250 -0.5749 0.02939 0.02402 -0.0047 1.0001 0.6527
-4.000 -0.5638 0.03069 0.02522 -0.0005 1.0001 0.6676
-3.750 -0.5521 0.03189 0.02633 0.0034 1.0001 0.6815
-3.500 -0.4986 0.03617 0.03040 0.0033 0.9779 0.7013
-3.250 -0.4707 0.03839 0.03250 0.0062 0.9663 0.7174
-3.000 -0.4378 0.04001 0.03398 0.0072 0.9571 0.7313
-2.750 -0.4150 0.04077 0.03462 0.0091 0.9478 0.7448
-2.500 -0.3891 0.04152 0.03525 0.0103 0.9387 0.7589
-2.250 -0.3580 0.04211 0.03570 0.0099 0.9315 0.7730
-2.000 -0.3367 0.04240 0.03590 0.0119 0.9224 0.7814
-1.750 -0.2970 0.04267 0.03603 0.0095 0.9154 0.7919
-1.500 -0.2765 0.04240 0.03566 0.0097 0.9044 0.8019
-1.250 -0.2480 0.04237 0.03553 0.0098 0.8951 0.8093
-1.000 -0.2134 0.04230 0.03534 0.0076 0.8870 0.8200
-0.750 -0.1934 0.04215 0.03514 0.0092 0.8772 0.8269
-0.500 -0.1544 0.04205 0.03492 0.0060 0.8711 0.8356
-0.250 -0.1383 0.04179 0.03463 0.0079 0.8604 0.8418
0.000 -0.1041 0.04161 0.03435 0.0056 0.8524 0.8502
0.250 -0.0750 0.04125 0.03394 0.0056 0.8427 0.8563
0.500 -0.0529 0.04102 0.03366 0.0055 0.8318 0.8649
0.750 -0.0106 0.04059 0.03317 0.0034 0.8258 0.8702
1.000 0.0056 0.04036 0.03291 0.0044 0.8144 0.8762
1.250 0.0495 0.03992 0.03242 0.0012 0.8095 0.8813
1.500 0.0663 0.03960 0.03209 0.0026 0.7972 0.8865
1.750 0.0921 0.03925 0.03172 0.0023 0.7869 0.8923
2.000 0.1322 0.03858 0.03102 0.0003 0.7800 0.8972
2.250 0.1536 0.03824 0.03068 0.0010 0.7684 0.9025
2.500 0.1986 0.03747 0.02989 -0.0019 0.7635 0.9070
2.750 0.2179 0.03710 0.02953 -0.0010 0.7509 0.9110
3.000 0.2715 0.03586 0.02829 -0.0046 0.7471 0.9141
3.250 0.2910 0.03543 0.02788 -0.0035 0.7339 0.9185
3.500 0.3428 0.03409 0.02655 -0.0068 0.7310 0.9218
3.750 0.3603 0.03377 0.02627 -0.0056 0.7178 0.9254
4.000 0.4145 0.03216 0.02469 -0.0089 0.7153 0.9286
4.250 0.4354 0.03159 0.02415 -0.0078 0.7023 0.9327
4.500 0.4934 0.02964 0.02224 -0.0114 0.6998 0.9357
4.750 0.5186 0.02890 0.02155 -0.0109 0.6867 0.9391
5.000 0.5553 0.02788 0.02057 -0.0119 0.6755 0.9421
5.250 0.6244 0.02599 0.01873 -0.0176 0.6692 0.9444
5.500 0.6599 0.02514 0.01791 -0.0186 0.6545 0.9477
5.750 0.7020 0.02424 0.01702 -0.0207 0.6384 0.9503
6.000 0.7534 0.02339 0.01613 -0.0245 0.6187 0.9523
6.250 0.7791 0.02308 0.01580 -0.0242 0.5957 0.9552
6.500 0.8212 0.02271 0.01532 -0.0267 0.5721 0.9579
6.750 0.8335 0.02271 0.01528 -0.0242 0.5498 0.9621
7.000 0.8684 0.02272 0.01516 -0.0257 0.5253 0.9648
7.250 0.8896 0.02292 0.01531 -0.0251 0.5025 0.9680
7.500 0.9091 0.02315 0.01547 -0.0242 0.4806 0.9715
7.750 0.9354 0.02344 0.01560 -0.0244 0.4586 0.9748
8.000 0.9513 0.02382 0.01600 -0.0232 0.4372 0.9790
8.250 0.9708 0.02423 0.01636 -0.0225 0.4175 0.9830
8.500 0.9968 0.02476 0.01681 -0.0231 0.3980 0.9863
8.750 1.0247 0.02536 0.01734 -0.0241 0.3794 0.9900
9.000 1.0496 0.02597 0.01790 -0.0246 0.3621 0.9941
9.250 1.0741 0.02663 0.01855 -0.0252 0.3452 0.9980
9.500 1.0808 0.02707 0.01902 -0.0225 0.3325 0.9999
9.750 1.0884 0.02766 0.01967 -0.0200 0.3201 0.9999
10.000 1.1026 0.02836 0.02040 -0.0188 0.3072 0.9999
10.250 1.1216 0.02913 0.02116 -0.0185 0.2945 0.9999
10.500 1.1472 0.02998 0.02192 -0.0192 0.2820 0.9999
10.750 1.1604 0.03091 0.02300 -0.0182 0.2705 0.9999
11.000 1.1765 0.03193 0.02413 -0.0177 0.2589 0.9999
11.250 1.1959 0.03291 0.02510 -0.0178 0.2476 0.9999
11.500 1.2189 0.03386 0.02599 -0.0183 0.2362 0.9999
11.750 1.2264 0.03514 0.02750 -0.0169 0.2262 0.9999
12.000 1.2435 0.03634 0.02873 -0.0168 0.2159 0.9999
12.250 1.2615 0.03744 0.02982 -0.0168 0.2057 0.9999
12.500 1.2681 0.03899 0.03163 -0.0156 0.1969 0.9999
12.750 1.2884 0.04024 0.03282 -0.0160 0.1877 0.9999
13.000 1.2946 0.04186 0.03464 -0.0149 0.1794 0.9999
13.250 1.3092 0.04347 0.03630 -0.0148 0.1710 0.9999
13.500 1.3162 0.04516 0.03812 -0.0140 0.1632 0.9999
13.750 1.3267 0.04701 0.04007 -0.0137 0.1559 0.9999
14.000 1.3303 0.04894 0.04218 -0.0128 0.1492 0.9999
14.250 1.3427 0.05071 0.04396 -0.0128 0.1426 0.9999
14.500 1.3387 0.05322 0.04675 -0.0117 0.1373 0.9999
14.750 1.3613 0.05442 0.04774 -0.0125 0.1302 0.9999
15.000 1.3477 0.05770 0.05144 -0.0112 0.1266 0.9999
15.250 1.3438 0.06045 0.05439 -0.0107 0.1220 0.9999
15.500 1.3646 0.06170 0.05545 -0.0115 0.1159 0.9999
15.750 1.3476 0.06568 0.05984 -0.0109 0.1133 0.9999
16.000 1.3357 0.06962 0.06407 -0.0109 0.1103 0.9999
16.250 1.3371 0.07237 0.06691 -0.0115 0.1066 0.9999
16.500 1.3523 0.07406 0.06853 -0.0121 0.1022 0.9999
16.750 1.3310 0.07938 0.07423 -0.0130 0.1005 0.9999
17.000 1.3098 0.08514 0.08031 -0.0146 0.0987 0.9999
17.250 1.2895 0.09116 0.08661 -0.0168 0.0969 0.9999
17.500 1.2717 0.09721 0.09288 -0.0194 0.0951 0.9999
17.750 1.3079 0.09548 0.09086 -0.0193 0.0892 0.9999
18.000 1.2776 0.10354 0.09927 -0.0230 0.0886 0.9999
18.250 1.2406 0.11335 0.10939 -0.0281 0.0886 0.9999
18.500 1.1929 0.12597 0.12230 -0.0353 0.0895 0.9999
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