FX 79-L-120 (fx79l120-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 79-L-120 (fx79l120-il) Reynolds number: 200,000 Max Cl/Cd: 43.89 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx79l120-il-200000-n5.txt Download as CSV file: xf-fx79l120-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 79-L-120
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
------ -------- --------- --------- -------- -------- --------
-15.750 -0.9155 0.11002 0.10587 0.0016 1.0000 0.0204
-15.500 -0.9599 0.09558 0.09120 -0.0076 1.0000 0.0203
-15.250 -0.9868 0.08612 0.08155 -0.0136 1.0000 0.0201
-15.000 -1.0126 0.07768 0.07289 -0.0188 1.0000 0.0202
-14.750 -1.0324 0.07091 0.06590 -0.0227 1.0000 0.0202
-14.500 -1.0497 0.06493 0.05968 -0.0258 1.0000 0.0204
-14.250 -1.0633 0.05978 0.05428 -0.0281 1.0000 0.0205
-14.000 -1.0724 0.05552 0.04984 -0.0298 1.0000 0.0209
-13.750 -1.0752 0.05225 0.04646 -0.0308 1.0000 0.0211
-13.500 -1.0778 0.04905 0.04312 -0.0315 1.0000 0.0212
-13.250 -1.0745 0.04687 0.04088 -0.0321 1.0000 0.0217
-13.000 -1.0738 0.04434 0.03822 -0.0324 1.0000 0.0222
-12.750 -1.0715 0.04208 0.03584 -0.0324 1.0000 0.0227
-12.500 -1.0683 0.03998 0.03358 -0.0321 1.0000 0.0232
-12.250 -1.0650 0.03792 0.03134 -0.0315 1.0000 0.0241
-12.000 -1.0595 0.03602 0.02925 -0.0306 1.0000 0.0246
-11.750 -1.0529 0.03429 0.02730 -0.0294 1.0000 0.0252
-11.500 -1.0456 0.03266 0.02557 -0.0280 1.0000 0.0258
-11.250 -1.0370 0.03138 0.02424 -0.0265 1.0000 0.0265
-11.000 -1.0275 0.03036 0.02315 -0.0248 1.0000 0.0273
-10.750 -1.0167 0.02927 0.02198 -0.0230 1.0000 0.0281
-10.500 -1.0035 0.02831 0.02090 -0.0214 1.0000 0.0296
-10.250 -0.9886 0.02724 0.01968 -0.0200 1.0000 0.0306
-10.000 -0.9745 0.02612 0.01850 -0.0185 1.0000 0.0319
-9.750 -0.9590 0.02520 0.01753 -0.0172 1.0000 0.0330
-9.500 -0.9422 0.02436 0.01665 -0.0159 1.0000 0.0344
-9.250 -0.9246 0.02353 0.01574 -0.0146 1.0000 0.0360
-9.000 -0.9056 0.02284 0.01491 -0.0135 1.0000 0.0379
-8.750 -0.8894 0.02189 0.01398 -0.0120 1.0000 0.0396
-8.500 -0.8707 0.02117 0.01323 -0.0108 1.0000 0.0416
-8.250 -0.8513 0.02052 0.01251 -0.0097 1.0000 0.0440
-8.000 -0.8317 0.01986 0.01178 -0.0085 1.0000 0.0464
-7.750 -0.8134 0.01912 0.01107 -0.0072 1.0000 0.0492
-7.500 -0.7933 0.01854 0.01044 -0.0061 1.0000 0.0522
-7.250 -0.7724 0.01803 0.00984 -0.0049 1.0000 0.0554
-7.000 -0.7536 0.01734 0.00921 -0.0036 1.0000 0.0593
-6.750 -0.7330 0.01683 0.00867 -0.0025 1.0000 0.0636
-6.500 -0.7127 0.01630 0.00812 -0.0013 1.0000 0.0683
-6.250 -0.6924 0.01578 0.00763 -0.0001 1.0000 0.0742
-6.000 -0.6719 0.01531 0.00716 0.0011 1.0000 0.0811
-5.750 -0.6515 0.01485 0.00674 0.0023 1.0000 0.0899
-5.500 -0.6242 0.01430 0.00624 0.0020 0.9876 0.1033
-5.250 -0.5868 0.01371 0.00575 -0.0005 0.9627 0.1262
-5.000 -0.5476 0.01307 0.00526 -0.0034 0.9365 0.1636
-4.750 -0.5092 0.01234 0.00476 -0.0062 0.9110 0.2197
-4.500 -0.4761 0.01161 0.00432 -0.0079 0.8845 0.2960
-4.250 -0.4480 0.01106 0.00406 -0.0082 0.8607 0.3747
-4.000 -0.4211 0.01079 0.00392 -0.0081 0.8399 0.4307
-3.750 -0.3947 0.01067 0.00383 -0.0076 0.8214 0.4682
-3.500 -0.3687 0.01061 0.00375 -0.0070 0.8051 0.4964
-3.250 -0.3429 0.01058 0.00367 -0.0064 0.7905 0.5190
-3.000 -0.3171 0.01057 0.00361 -0.0058 0.7773 0.5396
-2.750 -0.2915 0.01057 0.00357 -0.0051 0.7654 0.5581
-2.500 -0.2658 0.01057 0.00353 -0.0044 0.7543 0.5748
-2.250 -0.2399 0.01057 0.00350 -0.0038 0.7439 0.5902
-2.000 -0.2139 0.01059 0.00346 -0.0032 0.7345 0.6041
-1.750 -0.1876 0.01057 0.00344 -0.0026 0.7249 0.6147
-1.500 -0.1610 0.01057 0.00339 -0.0022 0.7167 0.6242
-1.250 -0.1344 0.01055 0.00335 -0.0018 0.7079 0.6327
-1.000 -0.1076 0.01055 0.00330 -0.0014 0.7001 0.6406
-0.750 -0.0808 0.01053 0.00328 -0.0010 0.6919 0.6481
-0.500 -0.0538 0.01054 0.00324 -0.0007 0.6848 0.6554
-0.250 -0.0269 0.01052 0.00324 -0.0003 0.6770 0.6623
0.000 0.0000 0.01055 0.00321 0.0000 0.6702 0.6702
0.250 0.0269 0.01052 0.00324 0.0004 0.6621 0.6768
0.500 0.0539 0.01054 0.00324 0.0007 0.6553 0.6848
0.750 0.0808 0.01053 0.00328 0.0010 0.6480 0.6920
1.000 0.1077 0.01055 0.00330 0.0014 0.6406 0.7001
1.250 0.1345 0.01055 0.00335 0.0018 0.6328 0.7079
1.500 0.1611 0.01057 0.00339 0.0022 0.6242 0.7166
1.750 0.1877 0.01057 0.00344 0.0027 0.6147 0.7249
2.000 0.2139 0.01059 0.00346 0.0032 0.6040 0.7344
2.250 0.2400 0.01057 0.00350 0.0038 0.5902 0.7438
2.500 0.2658 0.01057 0.00353 0.0044 0.5747 0.7543
2.750 0.2914 0.01057 0.00356 0.0051 0.5577 0.7657
3.000 0.3171 0.01057 0.00361 0.0058 0.5396 0.7776
3.250 0.3429 0.01057 0.00367 0.0064 0.5189 0.7906
3.500 0.3687 0.01061 0.00375 0.0071 0.4960 0.8051
3.750 0.3948 0.01067 0.00383 0.0076 0.4686 0.8212
4.000 0.4211 0.01079 0.00392 0.0081 0.4311 0.8397
4.250 0.4481 0.01106 0.00405 0.0083 0.3752 0.8607
4.500 0.4763 0.01161 0.00433 0.0079 0.2962 0.8848
4.750 0.5094 0.01234 0.00476 0.0062 0.2199 0.9113
5.000 0.5477 0.01307 0.00527 0.0034 0.1627 0.9366
5.250 0.5868 0.01371 0.00575 0.0005 0.1259 0.9627
5.500 0.6243 0.01430 0.00624 -0.0020 0.1034 0.9876
5.750 0.6515 0.01485 0.00674 -0.0023 0.0901 1.0000
6.000 0.6719 0.01531 0.00716 -0.0011 0.0810 1.0000
6.250 0.6925 0.01579 0.00763 0.0001 0.0743 1.0000
6.500 0.7127 0.01630 0.00812 0.0013 0.0684 1.0000
6.750 0.7331 0.01683 0.00867 0.0025 0.0636 1.0000
7.000 0.7537 0.01734 0.00921 0.0037 0.0592 1.0000
7.250 0.7725 0.01802 0.00985 0.0050 0.0553 1.0000
7.500 0.7934 0.01854 0.01044 0.0061 0.0521 1.0000
7.750 0.8135 0.01912 0.01106 0.0072 0.0489 1.0000
8.000 0.8318 0.01987 0.01178 0.0085 0.0463 1.0000
8.250 0.8514 0.02052 0.01251 0.0097 0.0440 1.0000
8.500 0.8709 0.02118 0.01323 0.0108 0.0416 1.0000
8.750 0.8895 0.02188 0.01398 0.0120 0.0396 1.0000
9.000 0.9058 0.02283 0.01490 0.0134 0.0378 1.0000
9.250 0.9246 0.02358 0.01577 0.0146 0.0361 1.0000
9.500 0.9423 0.02437 0.01665 0.0159 0.0343 1.0000
9.750 0.9592 0.02519 0.01752 0.0172 0.0329 1.0000
10.000 0.9746 0.02613 0.01850 0.0185 0.0318 1.0000
10.250 0.9887 0.02729 0.01971 0.0200 0.0307 1.0000
10.500 1.0039 0.02830 0.02089 0.0214 0.0296 1.0000
10.750 1.0169 0.02936 0.02207 0.0230 0.0283 1.0000
11.000 1.0277 0.03037 0.02317 0.0248 0.0273 1.0000
11.250 1.0375 0.03143 0.02429 0.0265 0.0265 1.0000
11.500 1.0461 0.03272 0.02564 0.0280 0.0259 1.0000
11.750 1.0535 0.03430 0.02730 0.0293 0.0253 1.0000
12.000 1.0600 0.03605 0.02928 0.0305 0.0246 1.0000
12.250 1.0650 0.03795 0.03138 0.0314 0.0238 1.0000
12.500 1.0693 0.03995 0.03356 0.0320 0.0233 1.0000
12.750 1.0727 0.04198 0.03572 0.0322 0.0225 1.0000
13.000 1.0744 0.04440 0.03829 0.0323 0.0222 1.0000
13.250 1.0780 0.04645 0.04042 0.0319 0.0216 1.0000
13.500 1.0797 0.04891 0.04294 0.0313 0.0211 1.0000
13.750 1.0774 0.05207 0.04622 0.0307 0.0209 1.0000
14.000 1.0724 0.05567 0.04996 0.0296 0.0206 1.0000
14.250 1.0628 0.06007 0.05460 0.0278 0.0205 1.0000
14.500 1.0503 0.06507 0.05982 0.0255 0.0204 1.0000
14.750 1.0313 0.07137 0.06638 0.0221 0.0202 1.0000
15.000 1.0134 0.07787 0.07307 0.0184 0.0202 1.0000
15.250 0.9871 0.08645 0.08189 0.0131 0.0201 1.0000
15.500 0.9516 0.09793 0.09362 0.0056 0.0201 1.0000
15.750 0.9096 0.11198 0.10786 -0.0031 0.0204 1.0000
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Polar data table (+)
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