NREL's S835 Airfoil (s835-nr) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: NREL's S835 Airfoil (s835-nr) Reynolds number: 100,000 Max Cl/Cd: 35.07 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s835-nr-100000-n5.txt Download as CSV file: xf-s835-nr-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S835 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.750 -0.5774 0.13952 0.13241 -0.0480 1.0000 0.1470
-15.500 -0.5999 0.13241 0.12526 -0.0501 1.0000 0.1531
-13.500 -0.8209 0.07787 0.07042 -0.0622 1.0000 0.2054
-13.250 -0.7909 0.08001 0.07259 -0.0601 1.0000 0.2061
-13.000 -0.7639 0.08189 0.07450 -0.0581 1.0000 0.2069
-12.750 -0.9456 0.05898 0.05127 -0.0625 1.0000 0.2210
-12.500 -0.9127 0.06087 0.05326 -0.0606 1.0000 0.2230
-12.250 -0.8943 0.06143 0.05386 -0.0589 1.0000 0.2254
-12.000 -0.9425 0.05559 0.04792 -0.0577 1.0000 0.2303
-11.750 -1.0257 0.04772 0.03977 -0.0554 0.9995 0.2352
-11.500 -1.0025 0.04704 0.03909 -0.0567 0.9964 0.2387
-11.250 -0.9771 0.04662 0.03868 -0.0580 0.9932 0.2424
-11.000 -0.9757 0.04428 0.03621 -0.0594 0.9883 0.2471
-10.750 -0.9943 0.04077 0.03241 -0.0604 0.9809 0.2519
-10.500 -0.9652 0.04057 0.03226 -0.0617 0.9782 0.2555
-10.250 -0.9528 0.03987 0.03155 -0.0611 0.9725 0.2590
-10.000 -0.9473 0.03857 0.03015 -0.0613 0.9668 0.2634
-9.750 -0.9578 0.03679 0.02817 -0.0595 0.9582 0.2675
-9.500 -0.9384 0.03604 0.02738 -0.0600 0.9536 0.2714
-9.250 -0.9094 0.03575 0.02710 -0.0614 0.9508 0.2755
-9.000 -0.9037 0.03495 0.02624 -0.0593 0.9434 0.2793
-8.750 -0.8869 0.03389 0.02501 -0.0598 0.9383 0.2843
-8.500 -0.8595 0.03330 0.02436 -0.0612 0.9353 0.2888
-8.250 -0.8487 0.03292 0.02400 -0.0590 0.9282 0.2920
-8.000 -0.8246 0.03241 0.02344 -0.0595 0.9239 0.2966
-7.750 -0.7978 0.03161 0.02248 -0.0611 0.9207 0.3023
-7.500 -0.7867 0.03110 0.02193 -0.0591 0.9135 0.3060
-7.250 -0.7609 0.03084 0.02171 -0.0594 0.9092 0.3100
-7.000 -0.7311 0.03042 0.02124 -0.0606 0.9061 0.3150
-6.750 -0.7128 0.02983 0.02053 -0.0601 0.9004 0.3202
-6.500 -0.6922 0.02944 0.02012 -0.0596 0.8948 0.3246
-6.250 -0.6628 0.02921 0.01991 -0.0604 0.8913 0.3289
-6.000 -0.6306 0.02882 0.01948 -0.0619 0.8886 0.3345
-5.750 -0.6163 0.02837 0.01892 -0.0605 0.8814 0.3397
-5.500 -0.5903 0.02814 0.01871 -0.0606 0.8768 0.3440
-5.250 -0.5595 0.02791 0.01852 -0.0616 0.8736 0.3490
-5.000 -0.5259 0.02752 0.01807 -0.0632 0.8711 0.3552
-4.750 -0.5117 0.02725 0.01771 -0.0617 0.8634 0.3604
-4.500 -0.4846 0.02713 0.01768 -0.0618 0.8589 0.3649
-4.250 -0.4531 0.02689 0.01744 -0.0628 0.8558 0.3706
-4.000 -0.4186 0.02648 0.01693 -0.0646 0.8534 0.3776
-3.750 -0.4029 0.02647 0.01697 -0.0629 0.8458 0.3820
-3.500 -0.3764 0.02637 0.01691 -0.0629 0.8408 0.3873
-3.250 -0.3444 0.02610 0.01661 -0.0641 0.8377 0.3940
-3.000 -0.3097 0.02578 0.01627 -0.0656 0.8353 0.4003
-2.750 -0.2909 0.02585 0.01641 -0.0643 0.8284 0.4051
-2.500 -0.2661 0.02577 0.01634 -0.0642 0.8226 0.4115
-2.250 -0.2337 0.02550 0.01601 -0.0654 0.8193 0.4189
-2.000 -0.1995 0.02531 0.01592 -0.0665 0.8168 0.4243
-1.750 -0.1629 0.02502 0.01564 -0.0681 0.8150 0.4312
-1.500 -0.1531 0.02526 0.01582 -0.0657 0.8042 0.4378
-1.250 -0.1222 0.02515 0.01583 -0.0662 0.8006 0.4432
-1.000 -0.0874 0.02491 0.01562 -0.0674 0.7980 0.4503
-0.750 -0.0495 0.02451 0.01517 -0.0693 0.7960 0.4585
-0.500 -0.0402 0.02497 0.01575 -0.0665 0.7854 0.4628
-0.250 -0.0089 0.02483 0.01566 -0.0670 0.7814 0.4696
0.000 0.0276 0.02448 0.01527 -0.0686 0.7788 0.4783
0.250 0.0637 0.02423 0.01513 -0.0697 0.7767 0.4842
0.750 0.1069 0.02449 0.01544 -0.0682 0.7619 0.4985
1.000 0.1417 0.02426 0.01532 -0.0690 0.7590 0.5045
1.250 0.1802 0.02393 0.01506 -0.0706 0.7568 0.5120
1.750 0.2226 0.02426 0.01550 -0.0686 0.7415 0.5253
2.000 0.2601 0.02394 0.01526 -0.0699 0.7385 0.5326
2.250 0.3029 0.02347 0.01480 -0.0724 0.7361 0.5418
2.500 0.3077 0.02412 0.01557 -0.0687 0.7238 0.5463
2.750 0.3443 0.02380 0.01534 -0.0697 0.7196 0.5534
3.000 0.3895 0.02324 0.01477 -0.0724 0.7165 0.5628
3.250 0.3974 0.02375 0.01542 -0.0691 0.7046 0.5674
3.500 0.4344 0.02339 0.01515 -0.0701 0.6992 0.5745
3.750 0.4837 0.02273 0.01450 -0.0734 0.6954 0.5838
4.000 0.4883 0.02328 0.01518 -0.0694 0.6823 0.5886
4.250 0.5315 0.02275 0.01473 -0.0713 0.6765 0.5957
4.500 0.5464 0.02303 0.01507 -0.0692 0.6644 0.6031
4.750 0.5866 0.02257 0.01468 -0.0707 0.6565 0.6099
5.000 0.6014 0.02283 0.01505 -0.0683 0.6440 0.6159
5.250 0.6445 0.02233 0.01457 -0.0703 0.6346 0.6242
5.500 0.6573 0.02264 0.01496 -0.0678 0.6201 0.6306
5.750 0.6818 0.02262 0.01503 -0.0667 0.6070 0.6367
6.000 0.7155 0.02238 0.01480 -0.0672 0.5934 0.6444
6.250 0.7326 0.02260 0.01506 -0.0654 0.5766 0.6517
6.500 0.7500 0.02277 0.01532 -0.0633 0.5595 0.6573
6.750 0.7698 0.02293 0.01551 -0.0617 0.5409 0.6644
7.000 0.7914 0.02310 0.01565 -0.0606 0.5201 0.6727
7.250 0.8081 0.02333 0.01590 -0.0584 0.4983 0.6781
7.500 0.8256 0.02361 0.01614 -0.0565 0.4745 0.6850
7.750 0.8423 0.02402 0.01647 -0.0548 0.4485 0.6932
8.000 0.8544 0.02452 0.01694 -0.0523 0.4220 0.6991
8.250 0.8657 0.02511 0.01745 -0.0497 0.3949 0.7058
8.500 0.8774 0.02582 0.01806 -0.0476 0.3672 0.7139
8.750 0.8859 0.02661 0.01877 -0.0449 0.3408 0.7202
9.000 0.8935 0.02749 0.01955 -0.0423 0.3159 0.7271
9.250 0.9029 0.02846 0.02042 -0.0402 0.2919 0.7351
9.500 0.9103 0.02945 0.02137 -0.0378 0.2695 0.7416
9.750 0.9178 0.03050 0.02237 -0.0356 0.2487 0.7490
10.000 0.9268 0.03165 0.02344 -0.0339 0.2286 0.7574
10.250 0.9333 0.03278 0.02455 -0.0316 0.2110 0.7640
10.500 0.9408 0.03399 0.02573 -0.0297 0.1943 0.7720
10.750 0.9489 0.03527 0.02697 -0.0281 0.1785 0.7801
11.000 0.9555 0.03655 0.02825 -0.0262 0.1646 0.7877
11.250 0.9637 0.03795 0.02962 -0.0249 0.1514 0.7968
11.500 0.9697 0.03932 0.03101 -0.0231 0.1398 0.8044
11.750 0.9765 0.04083 0.03252 -0.0218 0.1291 0.8137
12.000 0.9821 0.04238 0.03406 -0.0203 0.1198 0.8224
12.250 0.9884 0.04398 0.03569 -0.0190 0.1109 0.8323
12.500 0.9943 0.04555 0.03732 -0.0177 0.1030 0.8420
12.750 1.0002 0.04728 0.03909 -0.0167 0.0959 0.8531
13.000 1.0029 0.04909 0.04094 -0.0153 0.0903 0.8646
13.250 1.0075 0.05083 0.04277 -0.0141 0.0845 0.8777
13.500 1.0105 0.05268 0.04469 -0.0129 0.0796 0.8938
13.750 1.0121 0.05462 0.04670 -0.0118 0.0755 0.9171
14.000 1.0141 0.05636 0.04857 -0.0111 0.0713 1.0000
14.250 1.0198 0.05898 0.05118 -0.0116 0.0677 1.0000
14.500 1.0272 0.06149 0.05376 -0.0121 0.0635 1.0000
14.750 1.0323 0.06423 0.05651 -0.0127 0.0606 1.0000
15.000 1.0381 0.06694 0.05930 -0.0132 0.0575 1.0000
15.250 1.0418 0.06988 0.06223 -0.0139 0.0553 1.0000
15.500 1.0468 0.07277 0.06523 -0.0146 0.0525 1.0000
15.750 1.0498 0.07589 0.06837 -0.0154 0.0506 1.0000
16.000 1.0536 0.07897 0.07155 -0.0162 0.0485 1.0000
16.250 1.0563 0.08223 0.07489 -0.0172 0.0466 1.0000
16.500 1.0586 0.08553 0.07821 -0.0183 0.0452 1.0000
16.750 1.0607 0.08899 0.08180 -0.0194 0.0435 1.0000
17.000 1.0622 0.09257 0.08548 -0.0207 0.0420 1.0000
17.250 1.0638 0.09610 0.08906 -0.0221 0.0409 1.0000
17.500 1.0654 0.09969 0.09271 -0.0235 0.0398 1.0000
17.750 1.0651 0.10367 0.09686 -0.0252 0.0387 1.0000
18.000 1.0647 0.10769 0.10100 -0.0270 0.0377 1.0000
18.250 1.0649 0.11162 0.10500 -0.0290 0.0368 1.0000
18.500 1.0670 0.11517 0.10855 -0.0308 0.0360 1.0000
18.750 1.0613 0.12030 0.11388 -0.0335 0.0352 1.0000
19.000 1.0537 0.12584 0.11962 -0.0367 0.0344 1.0000
19.250 1.0462 0.13144 0.12539 -0.0401 0.0336 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NREL's S835 Airfoil (s835-nr)