NREL's S829 Airfoil (s829-nr) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NREL's S829 Airfoil (s829-nr) Reynolds number: 200,000 Max Cl/Cd: 47.5 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s829-nr-200000.txt Download as CSV file: xf-s829-nr-200000.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S829 Airfoil
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
------ -------- --------- --------- -------- -------- --------
-12.500 -0.4472 0.06094 0.05727 -0.1050 0.9713 0.0253
-12.250 -0.4702 0.05471 0.05088 -0.1066 0.9694 0.0249
-12.000 -0.4938 0.04966 0.04566 -0.1064 0.9649 0.0245
-11.750 -0.5764 0.05835 0.05400 -0.1019 0.9703 0.0253
-11.500 -0.5928 0.05374 0.04918 -0.1010 0.9648 0.0244
-11.250 -0.6050 0.04975 0.04491 -0.0995 0.9595 0.0237
-11.000 -0.6159 0.04616 0.04100 -0.0969 0.9543 0.0229
-10.750 -0.6280 0.04289 0.03737 -0.0929 0.9478 0.0222
-10.500 -0.6312 0.03950 0.03355 -0.0897 0.9436 0.0212
-10.250 -0.6322 0.03638 0.02996 -0.0860 0.9387 0.0206
-10.000 -0.6204 0.03383 0.02704 -0.0841 0.9350 0.0207
-9.750 -0.5974 0.03138 0.02426 -0.0838 0.9328 0.0212
-9.500 -0.5676 0.02936 0.02196 -0.0844 0.9310 0.0218
-9.250 -0.5374 0.02775 0.02015 -0.0849 0.9294 0.0238
-9.000 -0.5119 0.02620 0.01848 -0.0849 0.9269 0.0288
-8.750 -0.4923 0.02540 0.01760 -0.0841 0.9236 0.0327
-8.500 -0.4710 0.02417 0.01631 -0.0833 0.9211 0.0392
-8.250 -0.4531 0.02364 0.01570 -0.0821 0.9184 0.0479
-8.000 -0.4376 0.02276 0.01485 -0.0807 0.9162 0.0595
-7.750 -0.4258 0.02207 0.01419 -0.0786 0.9133 0.0721
-7.500 -0.4164 0.02150 0.01369 -0.0761 0.9098 0.0887
-7.250 -0.4073 0.02087 0.01317 -0.0736 0.9065 0.1124
-7.000 -0.3998 0.02013 0.01267 -0.0707 0.9036 0.1500
-6.750 -0.3961 0.01939 0.01227 -0.0673 0.9012 0.2124
-6.500 -0.4063 0.01920 0.01240 -0.0614 0.8964 0.2695
-6.250 -0.4199 0.01885 0.01239 -0.0546 0.8923 0.3376
-6.000 -0.4351 0.01824 0.01217 -0.0471 0.8889 0.4203
-5.750 -0.4670 0.01883 0.01291 -0.0363 0.8835 0.4445
-5.500 -0.3576 0.01954 0.01475 -0.0481 0.8880 0.7224
-5.250 -0.4037 0.02045 0.01573 -0.0349 0.8813 0.7339
-5.000 -0.4058 0.02130 0.01653 -0.0287 0.8779 0.7527
-4.750 -0.3728 0.02264 0.01773 -0.0285 0.8767 0.7690
-4.500 -0.5097 0.02206 0.01739 0.0014 0.8684 0.7712
-4.250 -0.5228 0.02269 0.01797 0.0094 0.8661 0.7864
-4.000 -0.5159 0.02352 0.01871 0.0140 0.8642 0.8030
-3.750 -0.1649 0.02754 0.02198 -0.0428 0.8759 0.8059
-3.500 -0.0959 0.02840 0.02271 -0.0499 0.8764 0.8103
-3.250 -0.0677 0.02890 0.02314 -0.0500 0.8754 0.8200
-3.000 -0.0129 0.02933 0.02347 -0.0550 0.8753 0.8247
-2.750 0.0149 0.02958 0.02366 -0.0553 0.8742 0.8337
-2.500 0.0312 0.03042 0.02448 -0.0535 0.8713 0.8402
-2.000 0.0086 0.03207 0.02614 -0.0396 0.8633 0.8608
-1.750 0.0567 0.03212 0.02613 -0.0441 0.8628 0.8638
-1.500 0.0910 0.03220 0.02618 -0.0460 0.8618 0.8692
-1.250 0.1220 0.03220 0.02613 -0.0473 0.8607 0.8753
-1.000 0.0461 0.03376 0.02776 -0.0283 0.8521 0.8886
-0.750 0.0872 0.03377 0.02774 -0.0315 0.8507 0.8914
-0.500 0.1214 0.03380 0.02775 -0.0335 0.8490 0.8953
-0.250 0.1367 0.03394 0.02787 -0.0318 0.8471 0.9020
0.000 0.1874 0.03376 0.02769 -0.0369 0.8464 0.9038
0.250 0.2371 0.03361 0.02755 -0.0419 0.8458 0.9060
0.500 0.1657 0.03471 0.02867 -0.0241 0.8352 0.9165
0.750 0.2116 0.03458 0.02854 -0.0283 0.8338 0.9183
1.000 0.2574 0.03444 0.02843 -0.0324 0.8327 0.9202
1.500 0.2471 0.03504 0.02905 -0.0216 0.8204 0.9300
1.750 0.2966 0.03481 0.02886 -0.0263 0.8190 0.9311
2.000 0.3472 0.03459 0.02870 -0.0312 0.8177 0.9324
2.250 0.3279 0.03497 0.02911 -0.0234 0.8070 0.9366
2.500 0.3727 0.03466 0.02886 -0.0269 0.8051 0.9381
2.750 0.3391 0.03503 0.02922 -0.0159 0.7939 0.9429
3.000 0.3957 0.03445 0.02872 -0.0214 0.7918 0.9435
3.250 0.4751 0.03323 0.02762 -0.0305 0.7904 0.9434
3.500 0.4969 0.03265 0.02712 -0.0295 0.7792 0.9452
3.750 0.6481 0.02807 0.02275 -0.0490 0.7783 0.9434
4.000 0.6933 0.02669 0.02149 -0.0516 0.7701 0.9450
4.250 0.7577 0.02429 0.01924 -0.0569 0.7649 0.9463
4.500 0.7907 0.02294 0.01799 -0.0570 0.7539 0.9480
4.750 0.8203 0.02162 0.01676 -0.0564 0.7422 0.9490
5.000 0.8439 0.02055 0.01579 -0.0549 0.7277 0.9503
5.500 0.8696 0.01921 0.01461 -0.0481 0.6791 0.9534
5.750 0.8783 0.01849 0.01370 -0.0434 0.5906 0.9549
6.000 0.8622 0.01921 0.01343 -0.0346 0.4499 0.9574
6.250 0.8380 0.02016 0.01394 -0.0254 0.3734 0.9593
6.500 0.8141 0.02085 0.01439 -0.0163 0.3259 0.9627
6.750 0.7893 0.02163 0.01495 -0.0074 0.2844 0.9658
7.000 0.7665 0.02241 0.01555 0.0011 0.2489 0.9696
7.250 0.7639 0.02355 0.01631 0.0048 0.1860 0.9720
7.500 0.7633 0.02456 0.01706 0.0083 0.1454 0.9743
7.750 0.7644 0.02550 0.01782 0.0118 0.1195 0.9767
8.000 0.7682 0.02636 0.01862 0.0149 0.1004 0.9797
8.250 0.7712 0.02719 0.01940 0.0182 0.0873 0.9825
8.500 0.7856 0.02807 0.02024 0.0192 0.0745 0.9840
8.750 0.7987 0.02908 0.02121 0.0204 0.0653 0.9856
9.000 0.8154 0.02974 0.02193 0.0211 0.0572 0.9874
9.250 0.8315 0.03085 0.02310 0.0222 0.0510 0.9892
9.500 0.8493 0.03165 0.02394 0.0229 0.0458 0.9913
9.750 0.8691 0.03290 0.02522 0.0236 0.0401 0.9928
10.000 0.8895 0.03382 0.02626 0.0240 0.0358 0.9942
10.250 0.9149 0.03556 0.02804 0.0237 0.0304 0.9950
10.500 0.9334 0.03658 0.02928 0.0242 0.0269 0.9966
10.750 0.9468 0.03753 0.03028 0.0248 0.0241 0.9985
11.000 0.9697 0.04038 0.03337 0.0248 0.0210 0.9992
11.250 0.9810 0.04232 0.03561 0.0266 0.0200 1.0000
11.500 0.9808 0.04416 0.03773 0.0302 0.0193 1.0000
11.750 0.9760 0.04608 0.03991 0.0342 0.0187 1.0000
12.000 0.9668 0.04811 0.04218 0.0385 0.0183 1.0000
12.250 0.9545 0.05003 0.04431 0.0431 0.0180 1.0000
12.500 0.9417 0.05147 0.04589 0.0474 0.0174 1.0000
12.750 0.9200 0.05435 0.04906 0.0525 0.0179 1.0000
13.000 0.8973 0.05675 0.05166 0.0575 0.0181 1.0000
13.250 0.8768 0.05848 0.05353 0.0620 0.0179 1.0000
13.500 0.8723 0.05782 0.05274 0.0654 0.0163 1.0000
13.750 0.8498 0.05990 0.05496 0.0698 0.0163 1.0000
14.000 0.8160 0.06399 0.05935 0.0737 0.0169 1.0000
14.250 0.7725 0.07059 0.06630 0.0758 0.0188 1.0000
14.500 0.7488 0.07528 0.07116 0.0759 0.0185 1.0000
14.750 0.6392 0.07870 0.07500 0.0734 0.0197 1.0000
15.000 0.6117 0.08394 0.08035 0.0727 0.0200 1.0000
15.250 0.5809 0.09056 0.08710 0.0702 0.0202 1.0000
15.500 0.5521 0.09759 0.09423 0.0667 0.0207 1.0000
15.750 0.5205 0.10502 0.10174 0.0627 0.0214 1.0000
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